Georgia Tech Sponsored Research 
Project E-16-N19 
Project director Mavris Dimitri 
Title System Definition & Module Development for 
Comprehensive Aircraft Sizing . . . 
Close-out 7/31/1999 
r NAG 1 1786 
System Definition and Module Development for a Comprehensive 
Aircraft Sizing and Synthesis Tool 
Year 1 Progress Report 
November 1996 
Dr. Dirnitri Mavris 
Principal Investigator 
Aerospace Systems Design Laboratory 
School of Aerospace Engineering 
Georgia Institute of Technology 
Atlanta, GA 30332-0150 
Summary Page ii 
Summary 
This report summarizes the efforts lo dale of the first year in the System Definition 
and Module Development for a Comprehensive Aircraft Sizing and Symhesis Tool contract 
(NAG 1 1786). This year's tasks were as follows: 
• Establish evaluation criteria amongst ASDL, NASA Langley SAB, and NASA 
Ames SAB 
• Receive training in the ACSYNT, FLOPS 
• Model various aircraft classes in each of the two synthesis codes 
• Analyze each of these aircraft in the synthesis codes and critique the codes based 
on the results (i.e. address fidelity issues, ease of modeling, etc.) 
• Examine the possibility of incorporating modules from existing programs 
• Suggest a system architecture for a next generation synthesis program 
To achieve these tasks, members from the ASDL traveled to both NASA Langley and 
Ames Research Centers to receive training and to develop evaluation criteria that meet the 
needs of the two centers. In addition, a visit was made to the Air Force's Wright 
Laboratory to receive training in ICAD and IDAS, two codes used by the Air Force with 
similar capabilities. These codes are being reviewed to establish a point of reference for 
military vehicle modeling and sizing. Based on these visits, evaluation criteria were 
established and a survey developed and distributed to the various users. The results from 
these surveys are still being collected and expected to be in the report by the end of this 
years effort. 
Three configurations are being modeled in ACSYNT and FLOPS at this lime. The 
configurations are the B747-400, C17, and F16C and represent baseline commercial and 
military configurations. The particular vehicles were selected based on data availability. 
The modeling is proceeding in two directions. First, an input deck is generated for each 
Summary 
Page (U 
configuration without the use of technology factors (adjustments, correlation factors). This 
will test the default prediction capabilities of the codes. Then, these factors are applied to 
test the ability for these codes to match the aircraft performance based on actual data for this 
configuration. Initial modeling results are presented in this report. Based on the modeling 
results and the user survey, a side-by-side comparison will be made of ACSYNT and 
FLOPS based on rankings from the evaluation criteria. 
To complement the aircraft modeling, scaling laws used by these codes to carry out 
the sizing function are investigated. Scaling laws prove to be essential in aircraft codes 
because they dictate the final configuration and performance. These sizing laws, in 
addition to the ability to integrate new technology modules, determine the applicability of 
the code to modeling revolutionary (versus evolutionary configurations). Sizing laws for 
ACSYNT and FLOPS are summarized in this report and a recommendation is made to 
model a futuristic fighter concept to test the response of these codes to such a futuristic 
concept. In closing, arguments are made to investigate modularity and the use of 
supporting code to facilitate analysis. 
Acknowledgments Page iv 
Acknowledgments 
This research could not have been completed without the dedication of a number of 
individuals. In particular, the graduate research assistants of the Aerospace Systems 
Design Laboratory at Georgia Tech, George C. Mantis, Noel I. Macsotai, Dan 
DeLaurentis, Michelle Kirby, Nathan Hint s, Jimmy Tai, Dani Soban, and Lance Bays. 
The project was overseen by ASDL research manager Dr. Dimitri Mavris and research 
engineer Dr. Mark Hale. 
Special thanks to the technical ."nonitor for the investigation, Dr. Gary Giles. In 
addition, this study could not have been executed successfully without the overview and 
assistance of the personnel of NASA Langley, Sam Dollyhigh, Amie McCullers; and 
NASA Ames. Tom Galloway, Paul Gelhaussen, Mark Moore, Andy, Halm, and Dave 
Kinney. Help from the following Air Force personnel at Wright Patterson is appreciated: 
Gordon Tamplin, John Cathey, Dave Hammond, and Terry Smith. Also, Dr. Bob 
Schwanz frorr Rockwell International is assisting in the acquisition of IDAS. 
Table of Contents Pagev 
Table of Contents 
Summary ii 
Acknowledgments v 
List of Illustrations vi
List of Tables vii
1. Introduction 1 
1.1. General Programming Structure 4 
1.2. Present Day Modular Strategies 5 
1.3. Analysis Strategies 8 
1.3.1. Analysis - Synthesis & Sizing 8 
1.3.2. Sensitivities 10 
1.3.3. Optimization
1.4. Modeling Strategies 1 
1.4.1. Calibration
1.4.2. Low Fidelity Trade Studies 12 
1.4.3. High Fidelity Trade Studies
1.4.4. Approximate Studies 3 
1.5. Surveyed Codes 14 
1.5.1. ACSYNT 5 
1.5.2. FLOPS 8 
1.5.3. ICAD 21 
1.5.4. IDAS 2 
1.6. Modeled Configurations 23 
2. Evaluation Criteria Survey 5 
3. Scaling Laws 7 
3.1. ACSYNT 2
3.1.1. Convergence
3.1.2. Optimization 9 
3.2. FLOPS 30 
3.2.1. Sizing (Analysis) Mode: IOPT=l, IANAL=3 3
3.2.2. Optimization mode: IOPT=3, IANAL=3 1 
3.2.3. Fuel Volume considerations 3
3.2.4. Fuselage "Design" 2 
4. Configuration Modeling 33 
4.1. Commercial Transport: B747-400 4 
4.1.1. ACSYNT
4.1.2. FLOPS 5 
4.2. Military Transport: C17 36 
4.2.1. ACSYNT
4.2.2. FLOPS 8 
4.3. Fighter: F16C 40 
4.3.1. ACSYNT 4 
4.3.2. FLOPS 6 
5. Results and Recommendations 48 
5.1. Side-by-Side Comparison
5.2. Isolation vs Supporting Tools 9 
5.3. Modeling of a Revolutionary Concept 50 
5.4. Independent Module Evaluation
6. References 52 
APPENDICES 3 
Table of Contents Page vi 
Appendix A. Survey 54 
Appendix B. B747-400 ACSYNT Input & Output File 55 
Appendix C. B747-400 FLOPS Input & Output File 6 
Appendix D. C17 ACSYNT Input & Output File 7 
Appendix E. C17 FLOPS Input & Output File 58 
Appendix F. F16C ACSYNT Input & Output File 9 
Appendix G. F16C FLOPS Input & Output File 60 
Appendix H. Side-by-Side Assessment Details 1 
Appendix I. IPPD Methodology 64 
List of Illustrations Page vii 
List of Illustrations 
Figure 1. Stand-Alone Code 4 
Figure 2. Sample Synthesis Toolkit 6 
Figure 3. Initial Configuration 1 9 
Figure 4. Modified and Sized Configuration' 9 
Figure 5. Using a Code for Calibration 12 
Figure 6. Using a Code for Low Fidelity Trade Studies 1
Figure 7. Using a Code for High Fidelity Trade Studies 3 
Figure 8. Using a Code for Approximate Studies 4 
Figure 9. ACSYNT Control Structure2 16 
Figure 10. FLight Optimization System-* 8 
Figure 11. FLOPS Module Capabilities 9 
Figure 12. ICAD 22 
Figure 13. IDAS System5 3 
Figure 14. Typical Relationship Between Calculated Weight and Estimated Weight2 28 
Figure 15. ACSYNT Weight Convergence Scheme 2
Figure 16. ACSYNT Wireframe Representation of C17 Model 37 
Figure 17. C17 Mission Profile 39 
Figure 18. F-16C Combat Air Patrol Mission ..41 
Figure 19. Store Configuration for the F-16C Combat Air Patrol Mission 43 
Figure 20. IPPD through Robust Design Simulation 64 
List of Tables Page viii 
List of Tables 
Table 1. Analysis Strategies 8 
Table 2. Modeling Strategies 11 
Table 3. Surveyed Codes 5 
Table 4. Modeled Configurations6 24 
Table 5. Survey Categories and Feedback 6 
Table 6. Suggested Design Variables in ACSYNT 30 
Table 7. FLOPS Optimization Design Variables 1 
Table 8. Status of Modeling 33 
Table 9. FLOPS Technology Factors 36 
Table 10. F-16C Geometry Input for FLOPS and ACSYNT 40 
Table 11. Engine Characteristics for the Fl 10-GE-100 2 
Table 12. F-16C Block 30 Combat Air Patrol Mission Weight Breakdown 44 
Table 13. Mission Time/Fuel Bum Comparison 46 
Table 14. Comparison of FLOPS Output to Actual Values 4
Table 15. Side-by-Side Assessment 49 
Introduction Page 1 
1. Introduction 
Significant investments have been made in the creadon and maintenance of aircraft 
sizing codes for use in early conceptual design activities. These codes permit a designer to 
rapidly trade-off new designs and perform mission analysis. FLOPS, ACSYNT, IDAS 
and ICAD are four leading synthesis and sizing codes used by government organizations 
within the US. The first two representing the only two "public domain" synthesis and 
sizing codes in existence outside of industry, which implies that they are the only ones 
available for government and academic use. These codes are described later in this section 
and will be the focus of this study. The effort for year one of this three year study has been focused on a side-by-side comparison of these codes as to independently quantify their 
differences and similarities; address issues associated with their for modeling accuracy, modularity, and user-friendliness; and identify possible shortcomings and suggest remedies 
to he carried out during subsequent phases of this study. This will eventually lead to a set 
of recommendations stating means by which these two programs can be enhanced to better 
serve the aerospace design community. 
These design tools may be considered as monolithic codes with an executive 
module managing a geometry and mission/sizing core with links to appropriate disciplinary 
modules. The executive has traditionally included the capability to do optimization and 
carpet plots in addition to single-point analysis. Graphical user interfaces have focused on 
geometric modeling and program control. These monolithic codes in general have been 
proven to have less modular capabilities when compared with modem-day programming 
techniques. To make up for these shortcomings, these codes are often not used in isolation 
but, rather, are combined with a number of supporting codes and used together as a 
system. For instance, FLOPS may be used in conjunction with RAPED, AER02S, and 
BDAP whereas ACSYNT may be combined with RAM, VORLAX, FELISA, and FPS3D 
depending on the level of desired analysis. This phase ofthe study will primarily focus on 
Introduction Page 2 
the examination of the capabilities of these monolithic codes while future studies will 
concentrate on testing these codes as they are used collaboratively with their supporting 
tools. 
Significant factors in the selection of a design code are in its prediction and 
modeling capabilities. This is directly related to the level of fidelity (measure of prediction 
accuracy of the final vehicle size, performance, etc.) of the analysis. Obviously, accuracy 
is an important issue when doing conceptual design because the decisions that are made in 
this phase lock in the major features of the configuration and have a significant impact in 
the life-cycle of the vehicle. These design codes have varying degrees of accuracy because 
the historical databases they were based on regression analysis for different vehicle classes 
using similar technologies and simplified empirical analysis methods. In recent years, 
many users have felt that FLOPS is more appropriately used for the modeling of transports 
while ACSYNT is centered around the prsdiction of advanced technologies for fighter 
aircraft (e.g. ASTOVL vehicles, advanced short takeoff and landing vehicles). During this 
phase of the study, three evolutionary vehicles, the CI 7, B747-400, and F16C are modeled 
in each code and the results compared side-hy-side in order to test the accuracy of the tools 
as compared to known data. These three configurations were selected primarily due to data 
availability. 
Another factor in the selection of a design code is user-friendliness. The term 
"user-friendliness" can include traits such as complexity of input, usefulness of defaults, 
input modification, etc. There are a number of disciplines that are required to be defined 
for proper vehicle analysis. This task can be quite complex and the number of variables 
overwhelming. Ideally, a code should have default settings that minimize initial user input. 
The prediction capabilities of a code based on defaults will be one part of this study. 
Another consideration is the level of difficulty to modify program inputs to match a 
particular configuration. Each of the codes that will be surveyed has some form of user 
interface that facilitates vehicle modeling, which includes disciplinary information as well 
Introduction Page 3 
as geometric modeling. A qualitative analysis of both the GUI and stand-alone interface will be done as the three selected configurations are modeled in-house and also based on 
user surveys. 
Given that these conceptual tools are the current baseline, it is important to 
understand that conceptual design is growing beyond the strict optimization and sizing for 
which these codes are based. Requirements are evolving to address such things as 
uncertainty and the need to include approximations of higher fidelity tools in earlier design 
processes. These requirements come from the need to perform an Integrated Product and 
Process Development (IPPD) approach in the early design phases. As IPPD will provide 
the impetus for innovation and technological advances during these early conceptual design 
phases, tools must also grow to accomrrodate these advances. Synthesis and sizing codes 
must thus be sufficiently modular so that they can accommodate these newer as well as 
future design techniques. During this phase of the study, the various disciplinary contributions/functions will be critiqued and modularity ofthe overall code assessed. 
An evolving vehicle base will also be required to be analyzed by these synthesis 
codes. Based on changing world threats, these codes must accommodate evolutionary as 
well as revolutionary configurations and technologies. These codes were developed during 
an era of strict evolutionary principles where statistical databases and sizing laws can be 
used effectively to analyze an appropriate aircraft configuration. Modem aircraft design 
requirements are providing these codes with configurations that are far outside of existing 
databases and technologies that are still developing. These revolutionary concepts will 
require that the modules have a strong, physics-based development so that their 
applicability remains valid for a larger pool of configurations. Because these concepts need 
to be included in the codes of the future, this study will also examine the vehicle scaling laws (e.g. how a vehicle configuration is changed internally by a code in order to fly a 
certain mission) that are inherent in each. In addition to looking at scaling laws, a highly-
maneuverable fighter concept from Lockheed, Ft. Worth, representative of futuristic 
Introduction Page 4 
configurations, will be modeled in each code during the later phases of this study. Also, 
the ability to integrate the required disciplinary modules to support the required technology 
developments based on physics will be investigated as discussed earlier. 
1.1. General Programming Structure 
Synthesis and sizing codes tend to be predominately in FORTRAN and are based 
on a master executive with a number of disciplinary modules. This is commonly referred 
to as a "Stand-Alone Version" and an example is shown in Figure 1 where a configuration, 
defined by an input file and auxiliary files (for engine decks, etc.), is analyzed and results 
written to an output file. To perform the analysis, a number of disciplinary modules may 
be called. A user has the capability to add additional disciplinary modules. This basic 
structure is common not only for various vehicle synthesis codes but for individual 
disciplinary tools as well. 
| Auxiliary Files 
Input Hie 
Namelist 
Formatted 
Siruclures/Weighis 
Propulsion User - Defined Modules 
Figurel. Stand-Alone Code 
These original sizing codes can be extended to include a Graphical User Interface 
(GUI), commonly referred to as the "Graphical Version", to make modeling and execution 
easier for the end user. The GUI complements the geometry routines in the original code 
with a visualization tool as well as enhances the executive. Also, he GUI helps a user in 
Introduction Page 5 
defining inputs and analysis post-processing. GUI's are written predominately in C and 
make use of the already existing sizing and disciplinary modules. 
In either version, the executive may also contain links for optimization and carpet 
plots. The optimization routines tend to be off-the-shelf, gradient-based optimizers. These 
optimizers favor well for traditional designs with limited search spaces as defined by a 
reasonably constrained problem. 
As a final note, the information structure for these codes plays an important role in 
modularity. Information is contained in and passed by global variables and/or common 
blocks. This makes information exchange easy programmatic ally. However, this type of 
information passing significantiy reduces the modularity and portability of the code. For 
instance, if a variable is added to a namelist in aerodynamics and the same namelist also 
appears in another disciplinary module, both modules must be re-compiled. Moreover, as 
any module changes the complete system must be re-linked. 
1.2. Present Day Modular Strategies 
A synthesis and sizing tool can be visualized as a number of analysis modules 
linked via a geometric modeling and mission analysis core, as shown in Figure 2. Modules 
can be added, deleted, or modified in response to analysis requirements driven by aircraft 
configuration and technology. The modules are executed in a problem dependent synthesis 
network and are controlled by synthesis and sizing drivers. This strategy has subtle 
differences from the codes dr.scussed earlier and shown in Figure 1 in that no strict 
coupling of the modules exists. The framework is plug-n-play instead of being compiled 
into a single monolithic executable. 
Introduction Page 6 
Figure 2. Sample Synthesis Toolkit 
Each module in the Synthesis Toolkit is a library of analysis programs. A particular 
choice of analysis program may be selected depending on problem analysis requirements 
and configuration, available data and files, find user preferences. Analysis modules can be 
interchanged as a design progresses from conceptual to preliminary to detailed design. 
Modules are determined by the particular problem to be analyzed or synthesized. In 
addition, new modules may be added as the level of detail in a design increases. For 
instance, initial weight estimates may be based on historical data and a module that 
determines weights based on production information could be integrated later. 
Notice that these modules are developed and analysis codes are selected 
independent from the software architecture. Codes will be validated and documented off 
line from the architecture by disciplinarians. After this process, these codes are integrated 
into the architecture. The synthesis network can be configured without having all of the 
Introduction Page 7 
codes in place. As codes are selected, the final data and analysis sequences are determined. 
Disciplinarians will still be required to maintain and enhance their respective analysis codes 
as well as provide expert advice, when needed, about the validity of information. The 
importance of an architecture that can be configured with minimal effort is emphasized by 
the need to incorporate future technologies as they are identified and developed based on 
needs of revolutionary configurations. These codes do not exist as preliminary vehicle 
performance assessments are made. Rather, estimates are used with the understanding that 
codes will be integrated if the technologies provide system level benefits. An architecture 
organized in this way is flexible because modules are organized to leave particular code 
selections open. 
Using this technique, generic synthesis templates can be developed based on 
aircraft configurations or corporate design practices. As shown in the lower right of Figure 
2, lower fidelity analysis codes comprise the inner ring of synthesis modules. As a design 
problem becomes increasingly more determinate, higher fidelity codes can be interchanged. 
This is emphasized by an outer ring of analysis codes. 
Response Surface Equations can be used to replace time consuming, higher-fidelity 
analyses. Or, they can be used to bring higher-fidelity information into design processes 
earlier. Usually, a concept progresses to a point where only a limited number of analysis 
cases are run on a detailed design. The number is limited by expense, man hours, and 
desired accuracy. These limitations can be overcome by systematically running a set of 
cases defined under the Response Surface Methodology (RSM) guidelines and by creating 
Response Surface Equations (RSE). In turn, RSE's can be substituted for analysis codes. 
This is shown in the lower right of Figure 2. There are at least two additional benefits 
gained from RSE's. The design space region of interest is continuous, allowing for robust 
design and simulation techniques to be used. Second, computational cost is reduced to the 
evaluation of algebraic expressions. An overview of a Response Surface Methodology is 
given in Appendix I. 
Introduction Page 8 
1.3. Analysis Strategies 
A designer can employ several different strategies for using these conceptual design 
tools depending on the desired analysis. These are summarized in Table 1. These 
strategies are clarified in the following sections. Some example scenarios where a designer 
would use one or more of these modeling strategies include: 
Scenario 1. Match and verify Fl 6 performance numbers —> Point Design Analysis 
Scenario 2. Study the effect of different scenarios on an F16-like vehicle 
-> Analysis, Sensitivity 
Scenario 3. Match a configuration in which all geometry is not known 
—> Sizing Analysis 
Scenario 4. Determining a new configuration that will meet a designated mission 
—> Sizing Analysis 
Scenario 5. Finalizing a design based on certain performance parameters 
—» Analysis, Optimization 
Scenario 6. Technology trade-offs on a vehicle design —> Sizing Analysis 
These scenarios demonstrate that one cr more analysis techniques can be utilized by these 
codes to achieve a certain design task. 
Table 1. Analysis Strategies 
Strategy Use 
Analysis (§1.3.1) 
Sensitivity (§1.3.2) 
Opti mization (§1.3.3) 
Determine vehicle performance and point designs 
Determine robustness to vehicle parameters 
Detenriine optimal vehicle parameters for a given mission 
1.3.1. Analysis - Synthesis & Sizing 
Synthesis involves the assembly of the effects of individual disciplines on the 
aircraft components so that performance characteristics about an aircraft can be obtained. A 
majority if not all of the vehicle parameters (geometry, mission, aerodynamics, propulsion, 
etc.) are known and input by the user. These parameters are normally enough for a sized 
configuration since the user also has the respective weights available to him. The 
difference between the final calculated and the known aircraft weights is an indicator of the 
Introduction 
Page 9 
prediction capabilities of the code. In this case, a user commonly applies scaling 
parameters (a.k.a. fudge factors) to his inputs so that values determined by the design code 
matches known data. The degree to which these values match is a measure of the code to 
accurately predict the behavior of the configuration. This is very important for the selection 
of which design code to use and is emphasized in this study. 
Design codes have the ability to size an aircraft so that specific mission 
requirements can be met. For example, a fuel balance is required to make sure that an 
aircraft can fly an extended-range mission. During this process, the design code must add 
and distribute fuel and apply appropriate scaling laws in order to assess mission 
performance. For example, additional fuel in the wings will require additional structural 
weight to support the fuel bladders. Depending on the scaling laws that are applied, 
radically different configurations may be obtained. 
This process may not be altogether automated and requires the expertise of a 
designer. An example is illustrated in Figure 3 and Figure 4. An initial configuration is 
shown in Figure 3 of an aircraft that is not capable of flying a transcontinental route. To 
meet this mission, a user would have to select different engines and increase the wing area 
as shown in Figure 4. Internal to the code, ACSYNT in this scenario, sizing occurred as 
fuel added and performance and disciplinary metrics were recalculated. 
Figure 3. Initial Configuration Figure 4. Modified and Sized 
Configuration1 
Introduction Page 10 
1.3.2. Sensitivities 
It is often of interest to determine the effect of changing a single decision variable 
on the gross weight and performance of the aircraft.2 Examples include determination of 
change in gross weight due to a prescribed change in physical parameters such as aspect 
ratio, or mission parameters such as range. Sensitivity may be simply referred to as the 
variation, or partial derivative, of one parameter with respect to another. For example, if 
the sensitivity of gross weight to wing thickness-to-chord ratio is negative, the gross 
weight may be reduced by increasing the thickness-to-chord ratio. However, it must be 
noted that an increase in thickness-to-chord ratio may reduce vehicle performance, violating 
performance constraints on the design. 
Sensitivity is also related to a robust design. It is desired that the sensitivity be as 
low as possible in order to produce a more robust design. Therefore, the impact of product 
variance will be minimized on eventual performance. 
1.3.3. Optimization 
The purpose of the optimization subprogram is to minimize or maximize some 
"objective11 function, subject to a prescribed set of hmits or "constraints" on the design.2 
For example, given a mission, the gross weight of the vehicle may be minimized subject to 
performance and zing requirements. The variables changed by the optimization program 
are referred to as design variables and include parameters such as wing area, aspect ratio, 
thickness-to-chord ratio, and vehicle thrust-to-weight ratio. In general, any variables input 
to a discipline module may be treated as a design variable and these variables are usually 
bounded to insure a valid design space. Functions which are evaluated by the modules 
such as gross weight, performance, parameters or fuel weight may be treated as parameters 
to be extremized in the objective function or may be constraints which he within prescribed 
bounds. This formulation allows for considerable latitude in choosing the objective 
function, decision variables and constraints. 
Introduction Page 11 
1.4. Modeling Strategies 
There are four basic modeling strategies that may be performed when using these 
sizing tools to predict aircraft performance. These are shown in Table 2. The differences 
in these strategies may be subtle at times but nonetheless important. For instance, 
designers often say they have modeled and studies a configuration (Low Fidelity Trade 
Study) when they have really matched their configuration (Calibration). 
Table 2. Modeling Strategies 
Strategy Use 
Calibration (§1.4.1) 
Low Fidelity Trade Studies (§1.4.2) 
High Fidelity Trade Studies (§1.4.3) 
Approximate Studies (§1.4.4) 
Match existing data and code validation 
Routine and rapid assessments 
Detailed or new technology assessments 
Robust simulation and design space search 
1.4.1. Calilb ration 
Calibration is done when matching industry provided data for future studies or for 
validating code modifications. As shown in Figure 5, the baseline configuration is 
modeled in the input files and the outpu: analysis and performance data is compared against 
known values. Typically, calibration is done in two stages. First, non-scaled parameters 
are used in order to determine the b£.sic prediction of the code. Then, input scaling 
parameters are used so that the prediction matches the known aircraft data. In this phase of 
the survey, the selected design codes will be used for "Calibration" so that the prediction 
capabilities can be assessed. 
Introduction Page 12 
•^^H^I^M I Ql/Jhil It : 
Figure 5. Using a Code for Calibration 
1.4.2. Low Fidelity Trade Studies 
During a low fidelity trade study, a baseline configuration is modeled and entered 
into the design code. The code sizes the configuration so that the vehicle can fly the 
prescribed mission, This is represented in Figure 6. The user frequentiy varies 
configuration variables (geometry, airfoils, engine parameters, etc.) and mission 
parameters as trade studies are performed. By doing this, different classes of vehicles can 
be developed and carpet plots and other post-processing can be done so that a concept 
selection processes can take place. 
Figure 6. Using a Code for Low Fidelity Trade Studies 
1.4.3. High Fidelity Trade Studies 
A designer may utilize disciplinary codes off-line from the design tool in order to 
provide higher fidelity analysis or prediction capabilities outside of those possible by the 
Introduction Page 13 
design code. This scenario is illustrated in Figure 7. These codes may be run off-line or 
they may be combined with the design tool in an automated system. For example, a user 
may use RAM to model an aircraft configuration and pass the configuration into FELISA to 
generate a CFD grid. In turn, FPS3D can be used to generate the appropriate polars 
required for the aerodynamics module in ACSYNT. 
£^jade Studies^ 
Figure 7. Using a Code for High Fidelity Trade Studies 
1.4.4. Approximate Studies 
During early conceptual design, a designer may wish to use approximate methods 
to reduce analysis time, facilitate program linking, and for robust simulation. In the 
example shown in Figure 11, Response Surface Equations can be used to approximate the 
design tool and higher-fidelity disciplinary analysis. Then, a Monte Carlo simulation can 
be used to determine a robust design based on probabilistic methods. The use of 
approximations, in this examples RSEs, gready reduces the amount of analysis time 
required. It is important to remember that approximate methods are valid in the domains of 
their approximations. A common approach for finding a design space is the use of 
screening tests which helps determine both the design space and to reduce the number of 
active design variables. 
Introduction Page 14 
Figure 8. Using a Code for Approximate Studies 
1,5. Surveyed Codes 
This study will involve four codes that represent the current state-of-the-art in 
conceptual design analysis. Each of these codes has a rather involved history and the 
current references are made with respect to the current versions at their respective centers. 
These four codes are shown in Table 3. The codes are described in the following sections. 
The remainder of this report will detar.1 specifics of each code in terms of modularity, 
prediction capabilities, and general usability. The configurations in this survey (B747-400, 
C17, and F16C) will only be modeled in ACSYNT and FLOPS at this time. ICAD has 
been acquired and users are still being trained. IDAS is still being acquired. Initial training 
in IDAS and ICAD has been received at ASC/XRED. Of the four codes, ICAD is the only 
one that is PC-Based. The others are workstation applications. 
Introduction Page 1\5 
Table 3. Surveyed Codes 
Code Version Center 
ACSYNT 3.0 NASA Ames Research Center 
Systems Analysis Branch 
FLOPS 5.85 NASA Langley Research Center 
Systems Analysis Branch 
ICAD - Air Force Air Systems Command (ASC) 
Technology Support Group (XRED) 
IDAS - Rockwell International 
1.5.1. ACSYNT 
AirCraft SYNThesis (ACSYNT) was originally created at NASA Ames Research 
Center in the early 70s to fulfill a need for the evaluation of advanced technologies on 
future aircraft and has been continuously enhanced and updated from that time forward. 
The ACSYNT Institute was founded in 1990 to advance the US capability for aircraft 
conceptual design and resided at the Virginia Tech CAD Laboratory. During this time, an 
interactive computer aided design interface to ACSYNT was developed and internal 
routines extended by the Institute. Institute control has been returned to the Systems 
Analysis Branch at NASA Ames and is also being co-developed by Phoenix Integration 
Systems in Blacksburg, VA. 
ACSYNT was designed to have the flexibility to analyze a wide range of civil and 
military aircraft, including fighters, bombers, and transports.2 ACSYNT is comprised of 
several discipline codes which can run either stand-alone for analysis of one aspect or be 
combined in order to evaluate the integrated results. As shown in Figure 9, these 
disciplines are Geometry, Weights and Structures, Aerodynamics, Propulsion, Takeoff 
Performance, Mission Performance, Cost, and Sonic Boom. ACSYNT includes a 
methodology for converging on a vehicle design and for optimizing the vehicle design for a 
particular objective function, subject to various constraints. 
Int, oduction Page 16 
CONTROL 
;ONVERGEKC= OPTJMIZATIOf SENSITIVITY 
GEOMETRY AERODYNAMICS PROPULSION STRUCTURES 
MASS PROPERTIES TRAJECTORIES ECONOMICS 
Figure 9. ACSYNT Control Structure2 
The COPES/CONMTN (Control Program for Engineering Synthesis/Constrained 
Minimization program) optimization package is used and is a part of ACSYNT. In order to 
provide the optimizer with feasible and realistic information, the discipline modules of 
ACSYNT are parameter driven and, where possible, based on theoretical models, as 
opposed to table look-ups. 
An interactive computer aided design (CAD) interface is also included in ACSYNT. 
This permits the execution and control of the process via interactive graphics menus and, 
by visual inspection of data and aircraft model shaded images, allows rapid evaluation of 
design configurations. This CAD system is coded in a 3-D graphics standard, PHIGS. 
Thus, ACSYNT is designed to be used on the new generation, high-speed workstations. 
The graphical user interface allows one to create/modify geometry, specify other non-
geometry inputs, execute a case, and generate graphs and plots of most numerical results of 
the analysis. Some limitations, however, do exist within the GUI which hmits its 
usefulness. Thus, ACSYNT is in the process of being equipped with a new geometry 
modeling capability, embodied in the Rapid Aircraft Modeler (RAM) tool. 
RAM is an interactive, parametric conceptual aircraft modeler that is useful for the 
generation of 3D designs for the conceptual design and optimization process. RAM is 
capable of producing geometries from which wetted surface areas, volumes, and volume 
distributions may be calculated. In addition, these models may be converted into gridded 
Introduction Page 17 
surfaces and used in later CFD analysis. Unlike the traditional CAD modeling, where 
geometries are defined by sets of points, RAM allows the designer to define the 
configuration by a set of parameters which drive the shape of the wing planform and 
fuselage. Currently, RAM supports NACA 4-series, biconvex, wedge, and input airfoil 
types. Fuselage and external stores are defined by a series of cross-sections along a spine. 
For engine nacelles, a subsonic convergent inlets and convergent axisymmetric nozzles 
may be modeled. Components can be translated, scaled, and rotated. RAM also has the 
capability for a user to define a digitized picture or drawing for a background. Using this, 
a designer can simply lay out components over the background until the vehicle is modeled. 
Modeling is executed in a GUI where changes in geometric parameters are updated 
on the screen in "real time". The graphics were written in GL, the SGI standard graphics 
library, and the GUI was created using FORMS, a public domain GUI builder and code 
generator. When completely integrated with ACSYNT, the user will have the capability to 
send a configuration generated in RAM directly to ACSYNT for analysis. 
To extend these capabdities major efforts are planned to enhance ACSYNT. Some 
are already underway. These include: 
• A parametric component modeler for enhanced usability (this effort is RAM 
which was described above and the development is underway); 
• Using beam theory to represent major aircraft components such as the wing: 
fuselage, and horizontal and vertical tail; 
• Integration of advanced propulsion analysis such as NEPP and the capability for 
parametric cycle analysis; 
• Basic InfraRed analysis; and 
• Stability and control estimation. 
Some of these have been implemented for irj-house use and will be transitioning to general 
distribution. 
Introduction Page 18 
1.5.2. FLOPS 
The NASA Langley developed FLight Optimization System (FLOPS) is a 
multidisciplinary system of computer programs for conceptual and preliminary design and 
evaluation of advanced aircraft concepts. It consists of nine primary modules: 1) weights, 
2) aerodynamics, 3) engine cycle analysis, 4) propulsion data scaling and interpolation, 5) 
mission performance, 6) takeoff and landing, 7) noise footprint, 8) cost analysis, and 9) 
program control.3 Version 5.85 is used in this study. 
Figure 10. FLight Optimization System3 
The capabilities of the individual modules are summarized in Figure 11. The 
weights module uses statistical/empirical equations to predict the weight of each item in a 
group weight statement. In addition, a more analytical wing weight estimation capability is 
available for use with more complex wing planforms. Centers of gravity and moments of 
inertia can also be calculated for multiple fuel conditions. 
Introduction Page 19 
Propulsion 
•MOST ADVANCED DISCIPLINARY MODULE 
• BASED ON QNEP, WITH 5 CYCLE DEFINITIONS 
AVAILABLE OR OPTION FOR USER DEFI NED 
• KEY CYCLE PARAMETERS CAN BE DESIGN VARIABLES 
DURING OPTIMIZATION 
• ENGINE SCALING 
Economics 
LCC, DOC, IOC can be calculated 
• Weight Based 
Accounts for engine/performance 
S tructures/W eights 
• NV STRUCTURAI ANALSYIS 
• WEIGHTS BASED ON GEOMETRY DRIVEN, 
HISTORICAL DATABASE (WITH ABOUT 25 FIGHTERS 
AND 17 TRANSPORTS) 
• 'TECHNOLOGY" FACTORS AVAILABLE 
V 
CYCLE PARAMS. M, H 
THNISUFT 
' GW, FNEJWT 
/ 
WEIGHTS, MISSION 
/ ECONOMICS 
COMP. WIS 
Mission Analysis/Sizing 
PERF: Sizing, mission performance 
GUID: simple cruise point opt,, 
optimal climb and descents 
S&C: None (DeLaurentis' work ?) 
RESULTS (WEIGHTS. PERT, ETC) 
DRAG 
GEOMETRY. M, VI SIZED AX 
I F 
uc, I 
[ANAL =3 
Aerodynamics 
• INTERNAL- EMPERICAL DRAG BUILD-UP TECHNIQUE 
• SKIN FRICTION COMPUTED INTERNALLY 
• EXTERNAL- "HOOKS" EXIST FOR USER DEFINED POLARS 
TO FUEL, PORF: NOISE 
Executive j 
• ANALYSIS TNNGT. 
• OPTIMIZATION 
•I/O 
Miscellaneous 
• TAKEOF&LANDING {NOT PART OF SIZING CYCLE) 
BASED ON FAR 25 OR MS-1793 
• NOISE, INCLUDING MULTIPLE SOURCES, SUPPRESSION, 
AND OBSERVER LOCATIONS 
Figure 11. FLOPS Module Capabilities 
The aerodynamics module uses a modified version of the EDET (Empirical Drag 
Estimation Technique) program to provide drag polars for performance calculations. 
Modifications include smoothing of the drag polars, more accurate Reynolds number 
calculations, and the inclusion of skin friction calculations. Alternatively, drag polars may 
be input and then scaled with variations in wing area and engine (nacelle) size. 
The engine cycle analysis module was developed by Karl Geiselhart and is base& 
on the QNEP program which is a modified version of NEPCOMP and its successors. It 
provides the capability to internally generate an engine deck consisting of thrust and fuel 
flow data at a variety of Mach-altitude conditions. Engine cycle definition decks are 
provided for turbojets, turboprops, mixed flow turbofans, separate flow turbofans, and 
turbine bypass engines, 
The propulsion data scaling and interpolation module uses an engine deck that has 
been input or one that has been generated by the engine cycle analysis module, fills in any 
missing data, and uses linear or nonlinear scaling laws to scale the engine data to the 
Introduction 
Page 20 
desired thrust. It then provides any propulsion data requested by the mission performance 
module or the takeoff and landing module. 
The mission performance module uses the calculated weights, aerodynamics, and 
propulsion system data to calculate performance. Based on energy considerations, 
optimum climb profiles may be flown to start of cruise conditions. The cruise segments 
may be flown at the optimum altitude and/or Mach number for maximum range or 
endurance or to minimize NOx emissions, at the long range cruise Mach number, or at a 
constant lift coefficient. Descent may be flown at the optimum lift-drag ratio. In addition, 
acceleration, turn, refueling, payload release, and hold segments may be specified in any 
reasonable order. Reserve calculations can include flight to an alternate airport and a 
specified hold segment. For supersonic aircraft, sonic boom overpressures are computed 
along the aircraft track using an approximate method. 
The takeoff and landing module computes the all-engine takeoff field length, the 
balanced field length including one-engine-out takeoff and aborted takeoff and the landing 
field length. The approach speed is also calculated, and the second segment climb gradient 
and the missed approach climb gradient criteria are evaluated. Insofar as possible with the 
available data, all FAR Part 25 requirements are met. The module also has the capability to 
generate a detailed take-off and climb-out profile for use in calculating noise footprints. 
The noise footprint module uses the takeoff and climb-out profile generated in the 
takeoff and landing module to compute noise footprint contour data or noise levels at user 
specified or FAA locations. It is based on the FOOTPR program. The noise sources 
include fan inlet and exhaust, jet, flap (for powered lift), core (combustor), turbine and 
airframe. Noise propagation corrections are available for atmospheric attenuation, ground 
reflections, extra ground attenuation, and shielding. 
Through the program control module, FLOPS may be used to analyze a point 
design, parametrically vary certain design variables, or optimize a configuration with 
respect to these design variables (for minimum gross weight, mmimum fuel burned, 
Introduction Page 21 
maximum range, minimum cost, or minimum NOx emissions) using nonlinear 
programming techniques. The configuration design variables are wing area, wing sweep, 
wing aspect ratio, wing taper ratio, wing thickness-chord ratio, gross weight, and thrust 
(size of engine). The performance design variables are cruise Mach number and maximum 
cruise altitude. The engine cycle design variables are the design point turbine entry 
temperature, the maximum turbine entry temperature, the fan pressure ratio, the overall 
pressure ratio, and the bypass ratio for turbofan and turbine bypass engines. 
1.5.3. ICAD 
ICAD is currendy being used at ASC/XRJED for concept evaluation. ICAD consists 
of a graphical interface called PARSET and an engineering analysis module as shown in 
Figure 12.4 PARSET has similar features to other modeling tools whereby a designer can 
specify a configuration in terms of parametric components. The parametric description is 
rather detailed since the PARSET is described in terms of pointwise hoops that are used in 
the analysis module. A feature that is found in PARSET and not in other applications is the 
ability to define relationships among parameters in the model via equations. For instance, a 
user can define an equation that specifies that the relative location of the landing gear on the 
aircraft. In addition to parametric components, a user also has the capabdity to use 
digitized profile and planform outlines or digitized cross-sections to define bodies. This 
simplifies vehicle configuration creation where geometry is relatively unknown, as is the 
case for competitors or threats. 
Introduction Pase 22 
Engineering Analysis 
Trade Studies 
Post Processing 
Figure 12. ICAD 
Unfortunately, little documentation is available about the system in terms of 
engineering analysis. However, significant effort has gone into the creation of post 
processing tools that are useful for decision making. Engine performance maps, carpet 
plots, excess power diagrams, and other plots can be obtained easily. This reduces the 
amount of effort required during data reduction. 
1.5.4. IDAS 
IDAS (integrated Design and Analysis System) is a system for the conceptual 
design and analysis of flight vehicles developed by Rockwell International.5 The system is 
a file-based and consists of the four modules: Configuration Development Module (CDM), 
Configuration Analysis Module (CAM), Parametric Synthesis Module (PSM), and 
Summary Report Module (SRM). The relationship among these modules in a conceptual 
design process is shown h; .-igure 13. A designer uses the CDM interactively to develop 
an aircraft configuration based on pre-defined component libraries. The CAM is used to 
perform weights and tierodynamic calculations. Parametric aircraft designs can be obtained 
from a baseline design using the interactive interface provided in the PSM. In addition to 
parametric studies based on typical configuration and performance parameters, the PSM 
allows for checks on constraint violations on a number of aircraft parameters as well as the 
capability to perform sensitivity studies. The final component of IDAS is the SRM which 
provides the tools needed by a designer to perform data visualization. These four modules 
PARSET 
Introduction Page 23 
interact with a file manager which catalogs files in a database as data, projects, or libraries. 
These modules are shown in Figure 13. The Level II programs are stand-alone programs 
that can be ran to generate information required by IDAS. 
Requirements 
Geometric Definition 
CDM I 
Baseline Analysis 
CAM I 
Pert o rm ance/Synthesis 
PSM I Kr 
Trade Summary/Evaluate 
SRM 
F 
I 
L 
E 
M 
A 
N 
-I A 
J G 
E 
Level II 
Proarams 
Database 
Intentionally 
Omitted 
•Data 
•Projects 
•Libraries 
Level II 
Intentionally 
Omitted 
Figure 13. IDAS System5 
Though some of the file-based technologies in IDAS have become outdated, the 
system provides some fundamental insight into mechanisms for cataloging files. The 
ability to efficientiy store and retrieve files limits the number of re-analysis and, therefore, 
reduces cycle time and expense, 
1.6. Modeled Configurations 
For this initial study, three configurations are being modeled and are shown in 
Table 4. These configurations are representative of the classes of vehicles that can be 
analyzed by these codes and are within the scope of this survey. Each configuration will be 
modeled in each of the four selected design codes (at the time of this progress report, they 
only have been modeled in ACSYNT and FLOPS) to gain insight into the workings of each 
of the codes. A highly-maneuverable fighter will be modeled in each code during later 
Introduction Page 24 
phases of this study. By modeling these configurations, the following are hoped to be 
achieved: 
• Side-by-side comparison of the codes in terms of accuracy and fidelity 
• Assessment of the modeling capabilities and limitations of each code 
• Ease of modeling in terms of user-friendliness 
• Comparison of the codes in isolation against using supporting disciplinary 
analysis codes 
• Investigate ability to model revolutionary vs evolutionary designs 
The actual modeling of each configuration will be discussed in more detail in Section 4. 
Table 4. Modeled Configurations6 
Commercial Transport: B747-400 
The largest airliner in the world, the 747-400 
possesses extended range and capacity compared to 
earlier 747 variants. The -400's wing features 
increased span and winglets. Typical 
accommodation is for 421 in three classes, with a 
maximum take-off weight over 800,000 pounds. 
Military Transport: C17 
The McDonnell Douglas C-17 Globemaster UI was 
designed for long-range and intra-theatre heavy cargo 
transport. Features include an externally blown flap 
system that helps provide the aircraft with STOL 
performance while carrying C-5 payloads. The 
structure of the C-17 is designed for survivability. 
Fighter: F16C 
An advanced version of the widely-used lightweight 
fighter, the F-16C has excellent ground attack, air-to-
air, and all-weather capabilities. The -C has 
improved take-off weight and maneuvering 
characteristics. The F-16 features a cropped delta 
wing with vortex control strakes blended with the 
fuselage. 
Evaluation Criteria Survey Page 25 
2. Evaluation Criteria Survey 
In an attempt to establish criteria amongst the ASDL, NASA Langley Systems 
Analysis Branch, and the NASA Ames Systems Analysis Branch for this research, visits 
were made by ASDL personnel to each of ihe branches. Discussions with both FLOPS 
and ACSYNT developers shed light on their approach to maintaining and improving the 
respective codes. In addition, ASDL personnel also visited ASC/XRED at Wright 
Patterson AFB in order to meet with ICAD and IDAS users and developers. Also, a list of 
issues and questions was generated by all parties to for the evaluation criteria needed for 
this study and eventually a user survey. As a final note, training was received by the 
developers during each of the visits as to the inner workings and modeling techniques used 
at these centers. 
Form these discussions, a user survey was generated that will provide feedback on 
the four design codes under study. The survey is provided in Appendix A. The survey is 
broken into the general categories shown in Table 5. The survey is currency being filled 
out by users across the country and results will be tabulated when they are returned. 
Additional surveys are being filled out by students at >'•-. Georgia Tech Aerospace Systems 
Design Laboratory so that new user feedback can be obtained. 
Evaluation Criteria Survey Page 26 
Table 5. Survey Categories and Feedback 
Category Desired Feedback 
Program Which analysis codes are used 
Program Ratings General ratings in for source code, 
documentation, studies, and usability 
Program Capabilities General questions regarding platforms, 
execution times, which analysis modes 
are used 
User Considerations Questions concerning the level of design 
expertise of the user filling out the 
questionnaire 
Developer Considerations Questions concerning the level of 
programming expertise of the user fdling 
out the questionnaire 
Input/Output Format and Considerations How is the program in terms of I/O 
capabilities 
Program Modules Individual disciplinary modules are rated for 
their overall effectiveness, fidelity, and 
shortcornings in modeling certain 
configurations 
Program Enhancements Additional modules and modifications by the 
user to provide capabilities that do not 
exist 
Vehicle Modeling Survey the types of vehicles that have been 
modeled and the accuracy of the 
prediction capabilities of the code 
Code Capability / Deficiency Rank 19 areas of future research that the 
user would like to see developed 
Scaling Laws Page 27 
3, SCALING LAWS 
The scaling laws within synthesis and sizing codes dictate the converged vehicle 
solution. Based on these laws, the code will size an aircraft until specific mission 
requirements can be met. During this process, the code will add and distribute fuel and 
apply appropriate scaling laws in order to assess mission performance. The eventual 
outcome is that the final vehicle configuration is direcdy effected by these laws and it is 
essential to understand how these laws vary between codes. 
3.1. ACSYNT 
Of the seven control options in ACSYNT, two are used primarily. These are the 
convergence option, which is equivalent to running ACSYNT in analysis mode, and the 
optimization, which allows an objective function to be maximized or minimized. 
3.1.1. Convergence 
To converge an aircraft, the user starts by entering the aircraft geometry and an 
estimated weight. ACSYNT then calls the Trajectory module, which, by additionally 
calling the Aerodynamics and Propulsion modules, calculates the mission performance at 
each mission point. The Weights module then calculates a new gross weight based on fuel 
needed and component butidups. The component buildups are calculated both as fractions 
of the gross weight and with empirical relationships. The initial estimate is then compared 
to the calculated weight, and if they do not agree to within a prescribed tolerance, the 
program iterates until the weights are converged. 
To do this, ACSYNT assumes that there exists a relationship between the estimated 
weight and the calculated weight. A typical relationship is shown in Figure 14. ACSYNT 
takes the initial estimate of the weight and plots it against the delta value between the 
estimated weight and the calculated weight (see Figure 15). The user inputs an initial slope 
value, and the program extrapolates from the point down to the Y=0 value, which will 
Scaling Laws Page 28 
correspond to zero delta between the two weights. (It is important to note two things about 
this slope value: the user inputs a positive value, yet the program algorithm necessitates a 
negative slope, as shown in the figure. The change is made internally. Also, the slope 
shown in Figure 14, which is in the documentation, is not equivalent to the slope the user 
needs to input. Together, these two inconsistencies, which are not documented, make 
understanding the convergence process very difficult for the new user.) 
CO 
SJ 
•a 
u 
EsSmaiedWaght, WMt 
Figure 14. Typical Relationship Berweeo Calculated Weight and Estimated Weight2 
CCD 
• D 
Input 3c£e\ Incut W=lc/fi 
rMcpdctetc 
Y=0 
Nswfelimcfec 
Figure 15. ACSYNT Weight Convergence Scheme 
The point where Y=0 is selected as the new estimated weight. The modules are 
again called to calculate a new weight, and the two values are again compared. If they are 
not within tolerance, the new estimated weight and the new delta are added as a new point 
on the graph, and either linear or quadratic interpolation is used to extrapolate a new value 
Scaling Laws Page 29 
for converged weight. This process continues until the weight is converged, or until the 
we:'.ght cannot be converged, in wl.ich case the weight is set at the maximum value input by 
the user. 
It is important to note that this method does not rely on knowing the exact shape of 
the curve that relates the estimated weight to the calculated weight. Therefore it is not 
necessary to carry empirical correlation data or equations as part of the source code. In 
addition, it is possible to converge new technology aircraft for which correlation data may 
be scarce, unattainable, or non-existent. Thus, the accuracy of the convergence depends 
heavily on the accuracy of the calculated weight. 
The documentation of the convergence is scarce and not easily understood. The 
actual convergence scheme cannot be deduced from the documentation provided. This 
becomes important when selecting appropriate input values, especially the slope (although 
the default value for slope is perfectly adequate and does not signiiicantiy impact either the 
time to converge or the accuracy of the convergence). The documentation in the source 
code is not adequate for rapid comprehension of the algorithms. 
3. i. 1. Optimization 
ACSYNT is capable of optimization through the use of the COPES/CONMEJif 
program. An objective function is the parameter which is to be minimized or maximized, 
and is a function of design variables. Design variables are those parameters that are 
allowed to be changed in order to optimize the objective function. They may consist of 
dependent or independent variables. Constraints must also be functions of the design 
variables, and are limited to a target value or a range of values. 
ACSYNT has the capability to use any of its 487 design variables as optimization 
variables. However, only one objective function may be optimized at a time. As a practical 
limit, no more than ten design variables should be used at a time. A list of the most 
common optimization variables are shown in Table 6. 
Scaling Laws Page 30 
Table 6. Suggested Design Variables in ACSYNT 
Variable Optimization Use 
Max Gross Weight Objective Function 
Aspect Ratio Design Variable 
Body Diameter, max Design Variable 
Body Lenth, max Design Variable 
Delta Fuel Volume Constraint 
Canard Area Design Variable 
Canard Sweep Design Variable 
Wing Area Design Variable 
Wing Sweep Design Variable 
Wing Root T/C Design Variable 
Wing Tip T/C Design Variable 
Wing Taper Ratio Design Variable 
Landing Thrust to Weight Constraint 
Engine Scale Factor Design Variable 
Wing Loading Constraint 
Aircraft Density Constraint 
3.2. FLOPS 
FLOPS will scale a configuration with respect to the following parameters in order 
to size an aircraft. Again, these parameters effect the final performance characteristics and 
i 
should be taken into account when designing a particular vehicle. 
3.2.1. Sizing (Analysis) Mode: IOPT=l, IANAL=3 
FLOPS flies mission and adds/subtracts fuel until the sizing converges. To do this 
component weights are calculated. There is no change in geometry except if I 
• Specify W/S, thus SW (wing area) changes as GW changes I 
• HTVC or VTVC > 0; respective tail area is changed to satisfy the input tail 
„„_. HTVC'SW^ISW/AR . 1jrr 
volume coefficient according to: SHT = for HT as an 
FusLength 
example 
Fuselage is unchanged; 
Scaling Laws Page 31 
3.2.2. Optimization mode: IOPT=3, IANAL=3 
During optimization, there are 11 design variables that are available. These are the 
only parameters that can be varied and they are given in Table 7. 
Table 7. FLOPS Optimization Design Variables 
Variable Effect 
AR Aspect ratio 
THRUST Thrust per engine or T/W 
SW Wing reference area or W/S 
TR Taper ratio 
SWEEP 1/4 chord wing sweep 
TCA Thickness / chord 
ETJT Engine Turbine Inlet Temp. 
EOPR Engine Overall Pressure Ratio 
EFPR Engine Fan Pressure Ratio 
EBPR Engine Bypass Ratio 
ETTR Engine Throttle Ratio 
The relationship between SW, AR, SPAN, and GLOV is as follows: AR = SPAN
2 /(SW - GLOV) 
where, GLOV is the portion above the outboard sweep line continued inboard. 
Mach number and altitude for mission segments can be optimized via the 
Performance Module. In this case: 
• Fuselage is unchanged; 
• Wing changes shape and size if appropriate optimization variables chosen 
• Tails change only as described in Sizing (Analysis) 
3.2.3. Fuel Volume considerations 
FLOPS sizing convergence is not dependent on having sufficient fuel volume. If 
there is insufficient volume, only a warning is issued. Fuel is carried as follows: 
• Wing: FULWMX (scales with AR, SW, TR, SPAN) 
Scaling Laws Page 32 
( 
FULWMX = FWMAX • TCA • SW 2\ 1 — TR 
(1 + TR2) SPAN 
• Fus.: FULFMX (fixed, unless LFUFU =1) 
• If IFUFU= 1, fuselage fuel capacity is adjusted to meet fuel reqmts. 
• External tanks: FULAUX (fixed) 
3.2.4. Fuselage "Design" 
If user does not input fuselage length and width, FLOPS will calculate them if 
given the following information: 
• FPLTCFf (1 st class seat pitch) 
• TPLTCH (Tourist class seat pitch) 
• NFABR (# 1st class seats abreast) 
• NTABR (# Tourist class seats abreast) 
If needed, FLOPS will form a second deck. 
Configuration Modeling Page 33 
4. CONFIGURATION MODELING 
Three configurations have been modeled in ACSYNT and FLOPS. At the writing 
of this interim report, ICAD has been acquired and users are still being trained. IDAS is 
still being acquired. Initial training in IDAS and ICAD has been received at ASC/XRED. 
The present status of the modeling is summarized in Table 8. Cost estimation is not being 
considered at this time. 
Table 8. Status of Modeling 
B747-400 C17 F16C 
ACSYNT 
Mission V V 
Geometry V V 
Aerodynamics 
Structures/Weights V V 
Propulsion V V V 
Performance Matching V 
FLOPS 
Mission V V 
Geometry V 
Aerodynamics 
S tructuresAV eights 
Propulsion 
Performance Matching 
ICAD Not Modeled at This Time 
IDAS Not Modeled at This Time 
Configuration modeling is being done in two directions. First, the baseline 
configuration is direcdy entered into the design codes and analysis and performance values 
are obtained. This will test the. non-scaled prediction capabilities of the codes. These 
results vary because these codes have different analysis routines and estimations based on 
different assumptions and historical databases. Second, appropriate factors can be applied 
based on the non-scaled numbers so that the performance can be matched to known data. 
Configuration Modeling Page 34 
Using these results, it will be possible to assess the types of and the degree of accuracy of 
the analysis and performance data. 
The results in this progress report are non-proprietary. Input and output files from 
ACSYNT and FLOPS are given in Appendices B - G. These files contain the non-scaled 
technology factors. Performance for some of the configurations is still being matched so 
scale factors are not yet appropriate. Al: the time of the final report, a second document will 
be provided that contains any proprietary information. 
4.1. Commercial Transport: B747-400 
4.1.1. ACSYNT 
Information for the Boeing 747 was obtained both from Jane's All The World's 
Aircraft and from several existing ACSYNT 747 models of known fidelity. The matched 
model was completed first. The unmatched model was then created by deleting matched 
information and letting ACSYNT calculate the missing parameters based on its internal 
algorithms. First, the geometry was checked and found consistent with information in 
Jane's. As in the C17, the wing lets w^re not explicitiy modeled in the geometry; rather, 
the aerodynamic coefficients were changed to reflect their effects. Next, the existing 
ACSYNT models were compared for inconsistencies and/or completeness of information. 
For example, the weight slopes were found to be fixed in one model, and the weights 
themselves fixed in another. Although these two methods produced identical results, the 
slope factors were retained in order to allow other factors in the modeling to possibly affect 
the weight. Aerodynamic data was relatively consistent between the models, but one model 
had drag slope factors included and these were incorporated into the new model. A new 
mission was created to match the mission run in the FLOPS 747 case. The economic 
analysis of the model was not included. 
Configuration Modeling Page 35 
4.1.2. FLOPS 
The Boeing 747-400 derivative modeled in FLOPS was based on the 412 passenger 
capacity, 7,300 nm mission with a cruise Mach number of 0.85 and altitude of 40,000 ft. 
The input file was a derivative of work performed by the Systems Analysis Branch at 
NASA Langley. The original file contained all pertinent information (geometry, 
aerodynamic drag polars, etc.) except for the engine definition. The engine used to size the 
B747-400 was the Pratt&Whitoey 4056. The engine information was obtained from 
NASA Lewis and in a form compatible with the FLOPS engine analysis routines. 
The B747-400 was sized based on a weight breakdown definition. Actual 
component weights were specified and FLOPS was manipulated to achieve those goals. 
The manipulation was accomplished through component weight factors. Within the 
FLOPS input namelists, factors exist which will either increase or decrease the resulting 
weights determined by the internal equations. These factors scale the results up or down 
depending upon the actual numbers needed. In this case, fourteen factors were utilized to 
either reduce or increase the component weights. The factors and a description are listed in 
Table 9. The resulting sized aircraft was less than 5,000 pounds from the actual aircraft. 
All component weights deviated from the actual values by less than 1%. 
Configuration Modeling Page 36 
Table 9. FLOPS Technology Factors 
Namelist Name Variable Parameter 
WTLN Wing FRWI 1.015 
Horizontal Tail FRHT 0.8 
Vertical Tail FRVT 0.9 
Nose Landing Gear FRLGN 1.5 
Main Landing Gear FRLGM 1.7 
Nacelles FRNA 1.45 
Miscellaneous WPMSC 0.65 
Surface Controls FRSC 1.55 
Auxiliary Power Unit WAPU 0.9 
Instruments WIN 1.0 
Hydraulic Systems WHYD 1.3 
Electrical Systems WELEC 0.8 
Avionics WAVONC 1.7 
MISSIN Fuel Flow Factor FACT 1.025 
4.2. Military Transport: C17 
4.2.1. ACSYNT 
The information used to model the McDonnell Douglas CI7 came from both 
published sources (such as Jane's All the World's Aircraft and Aviation Week and Space 
Technology) and from McDonnell Douglas directly. The amount and integrity of the 
information provided was such that a matched ACSYNT model of the aircraft was 
completed first. The fixed information was then stripped from the model and ACSYNT 
was allowed to calculate as much of the missing information as possible to create the 
unmatched model. 
The first step was to model the aircraft's geometry. While a rather sophisticated 
model may be created using the graphics interface to the code, ACSYNT is somewhat 
limited in what it can and cannot analyze from a geometric point of view. For example, 
ACSYNT does not currently model winglets. However, effects of winglets may be 
included numerically in the aerodynamics module by adding a multiplicative factor to the 
coefficients of lift and drag. The wireframe geometry of the model used in ACSYNT is 
Configuration Modeling Page 37 
shown in Figure 16. Note, for example, the geometric lack of dihedral. Yet dihedral is a 
numerical input to the code, and its effects computed in the aerodynamics. 
After the geometric model of the aircraft was completed, propulsion data, 
aerodynamic data, weights, and mission data were added. Propulsion data was gathered 
from published sources, as well as some basic information provided by McDonnell 
Douglas. Aerodynamic data was provided by McDonnell Douglas in the form of some 
drag polars, Cl-alpha curves, and a parasite drag breakdown. The engine exhaust over the 
blown flaps provided a significant amount of lift, but as a direct function of thrust. 
Difficulty arose in precisely matching the aerodynamics because of this coupled nature of 
the thrust and lift. This resulted in some rather unusual drag polars, in which the drag 
curves and Cl-alpha curves were differentiated by a dimensionless drag coefficient. 
Attempts to extract Mach numbers out of these thrust coefficients led only to the conclusion 
that the curves provided were probably conducted at very small Mach numbers, not in the 
flight regime of interest (cruise). This precluded their use. ACSYNT, however, provides 
scaling factors that allow the user to change the aerodynamics to model effects such as the 
blown flaps. If the effect on lift and drag is known, the aerodynamic quantities may be 
scaled accordingly. 
Figure 16. ACSYNT Wireframe Representation of C17 Model 
Configuration Modeling Page 38 
For the matched model, component weights were fixed based on component 
weights of similar aircraft and best engineering judgements. ACSYNT was then executed 
to converge the weight of the aircraft. The converged weight was very close to the actual 
weight of the aircraft due to the fixing of the component weights. 
Given the accuracy of the data, the matched model turned out well. ACSYNT 
provides technology factors that allow scaling of results to correspond to given data. The 
initial input process was relatively simple. Matching the scaling factors, however, was not 
easy and analyzing the output file to identify the results was difficult. 
After the matched model was completed, much of the fixed data was stripped out in 
order to check the accuracy of the equations in ACSYNT. The geometry remained the 
same. The fixed weights were completely removed, except the payload. Aerodynamics 
still needed a CI max. The propulsion was modeled using the General Electric CF6-80C2 
as a baseline engine and using its cycle analysis parameters. The engine was then scaled to 
provide the thrust required. Three basic missions were performed. Each consisted of a 
climb segment, a cruise segment at altitude and with payload, a beam-down descent and 
unloading of payload, a second climb and cruise segment, and a final descent. Each 
mission had a specified payload and a range. 
4.2.2. FLOPS 
The McDonnell Douglas C-17 transport was modeled in FLOPS based on nonj-
proprietary information. Three missions were selected: 
• 2500 nmi range, 124,000 lbs. payload 
• 4600 nmi range, 50,000 lbs. payload 
• 3900 nmi range, 112,000 lbs. payload 
The range in each includes a 500 nmi leg to an alternate airfield for refueling. For each 
mission, the cmise conditions were specified at 28,000 ft. altitude and 0.75 Mach number. 
Configuration Modeling Page 39 
In FLOPS, these values were fixed and the mission segments were optimized for minimum 
fuel flow. The mission profile is included in Figure 17. 
A problem arises because in FLOPS only one takeoff and one landing can be modeled; 
there is no capability for multiple take-offs and landings. Therefore, one specifies a 
refueling segment with a negative amount of fuel added to simulate the "middle" descent, 
landing, taxiing, takeoff, and climbout. The negative fuel added corresponds to the fuel 
needed to perform these mission segments. 
I 
As all propulsive data are proprietary, no engine deck was available. Therefore, the 
internal engine modeling capability of FLOPS was utilized. FLOPS provided several 
different types of powerplants, including a twin-spool bypass turbofan engine, like that 
used on the C-17. Basic parameters, such as overall pressure ratio and fan bypass ratio, 
were input. Modeling engines in this manner is fairly straightforward. 
All other inputs were starightforward, and performed as specified in the FLOPS 
manual. The only other difficulty came with the JJRW switch in the MISSION definition 
namelist. This swtich is set to either fix the aircraft weight, and calculate range based on it, 
or vice-versa. Initially, this was set to fix the weight, resulting in several cases of the 
aircraft failing at some point along the mission. In this mode, FLOPS is extremely sensitive 
4. Descent 
X nmi 500 nmi —*\ 
Figure 17. C17 Mission Profile 
Configuration Modeling Page 40 
to the input design gross weight. If input too high, the aircraft will not be modeled; too 
low, and the program provides erroneous output. Simply setting this to fix the range at the 
input value, and sizing the aircraft's weight accordingly, fixed this problem - FLOPS 
successfully modeled the aircraft on the first attempt thereafter. 
4.3. Fighter: F16C 
The characteristics for the F-16C were taken from Standard Aircraft Characteristics 
for the F-16C Fighting Falcon for Block 30 through Block 30C. This document outlines 
the basic dimensions, weights, engine characteristics, loading and performance 
characteristics for various missions. Please refer to Table 10 for the some of the geometric 
characteristics of the F-16C. 
Table 10. F-16C Geometry Input for FLOPS and ACSYNT 
Group Parameter Value Unit Group Parameter Value Unit 
Fuselage Overall Length 49.3 H. Tail Area 63.7 feetz 
Overall Height 16.6 feet Aspect Ratio 2.114 
Width 3.8 feet Taper Ratio 0.39 
Sweep (L.E.) 40.0 
Wing Area 300.0 feet2 Airfoil 4.5 % thick 
Span 30.0 feet V. Tail Area 54.75 feet2 
Aspect Ratio 3.0 Aspect Ratio 1.294 
Taper Ratio 0.2275 Taper Ratio 0.437 
Sweep (L.E.) 40.0 degrees Sweep (L.E.) 47.5 degrees 
Airfoil 4.0 % thick Airfoil 4.0 % thick 
In addition, mission time, fuel burned and distances for these missions were 
provided. These missions included: Air Superiority, Air to Ground, Minimum Time 
Intercept, Close Air Support, Combat Air Patrol (CAP), and Ferry. The mission used to 
compare ACSYNT and FLOPS was the CAP mission. This demanding mission tests the 
performance of the F-16C at a variety of operating conditions. The details of mission are 
outlined in Figure 18. 
Configuration Modeling Page 41 
45,600 ft 
* Reserve fuel for 20 min Loiter at Sea Level 
Figure 18. F-16C Combat Air Patrol Mission 
The total block time for this mission was 229.8 minutes (3.833 hours) and the 
block range was 644 nautical miles. Several mission rules were outlined in order to further 
specify how the mission segments were to be flown in ACSYNT and FLOPS. Naturally, 
the manner in which the mission was defined by each code differed, so these rules helped 
to maintain consistency between the codes. The mission rules are as follow: 
1. Takeoff Fuel Allowance: 6 minutes of operation at sea level with a power 
setting equivalent to T/W=0.2. One minute allocated for takeoff run at mjUitary 
(maximum dry power) thrust setting and climbs at military thrust setting. 
2. No distance credit for takeoff, landing, loiter, combat maneuvers, or descents. I 
3. Cruises occur at speed and altitude for maximum range, with 50,000 ft as the 
maximum cruise altitude. 
4. External fuel tanks are dropped when the weight of mission fuel burned equalt 
the weight of external fuel. The pylon is retained for the external centerline fuel 
tank. 
Configuration Modeling Page 4^2 
5. Combat occurs at M = 0.9,10,000 feet, and for a sustained turn at a load factor 
of 5 g's 
6. No time or distance credit for expending stores. 
7. Return climbs are at military power from the post combat altitude. 
8. Landing fuel allowance of 20 minutes loiter at best endurance Mach at sea level. 
9. Ammunition casings are not expended, but are included as weight carried 
throughout the mission. 
For a consistent comparison of mission performance, engine characteristics should 
match. There were several problems in getting consistent propulsion characteristics for use 
in FLOPS and ACSYNT. The F-16C currently utilizes either the General Electric F110-
GE-129 (GE129) turbojet engine or the Pratt & Whitney F100-PW-229 (PW229) turbojet 
engine. Both of these produce roughly the same maximum amount of uninstalled sea level 
static (SLS) thrust. The GE129 produces roughly 29,500 lbs of thrust at these conditions, 
while the PW229 produces 29,000 lbs of thrust. After considering installation losses for 
the GE129, the SLS thrust drops to 25,150 lbs. However, the baseline model for the F-
16C utilized an F110-GE-100 (GE100), precursor of the GE129, which produces 24,850 
lbs of installed thrust at SLS. Please refer to the summary in Table 11 for the specifications 
of the GE100 power plant: 
Table 11. Engine Characteristics for the Fl 10-GE-100 
Power Plant F110-GE-100 
Manufacturer General Electric Aircraft Engines, Cincinnati, OH 
Type Twin Spool Axial Flow Turbofan 
Length w/ Afterburner 182.3 in 
Weight (Dry) 3,911.1 lbs 
Inlet Normal Shock (826.7 in2) 
Nozzle Convergent-Divergent Variable Geometry 
Augmentation Afterburner 
At the time of modeling, a GE100 engine deck was not available. This engine was 
simulated in ACSYNT using the internal analysis by letting it scale the engine to the 
Configuration Modeling Page 43 
appropriate thrust rating. The GE129 in the form of a look-up table was used for the 
FLOPS analysis. This seems to be an inconsistency, and is thus noted, but at the time of 
modeling there were considerable difficulties in making ACSYNT accept the GE129 engine 
deck. The most appropriate comparison would be to use the same look-up tables for both 
codes. At present, it would seem that FLOPS has a slight advantage in the propulsion 
system equal to 300 lbs thrust at sea level. 
The stores for the F-16C were configured for the CAP mission as shown Figure 
19. Two AIM-9's were installed on the wingtip launchers at stations 1 and 9. 
Aerodynarnically, this is considered to be the baseline configuration for store drag. 
Additional stores incrementally add drag to this baseline configuration. In addition to the 
wingtip AJM-9's, two AIM-120's were installed on wing launchers at stations 2 and 8. 
Two 370 gallon external fuel tanks at stations 4 and 6, and one centerline 300 gallon tank at 
station 5 supplement internal fuel capacity. 
Station Location for the F-16, Looking Forward 
Figure 19. Store Configuration for the F-16C Combat Air Patrol Mission 
The component weight breakdown for the configuration shown in Figure 19 is 
summarized in Table 12. The empty weight for the CAP mission configuration is 17,787 
Configuration Modeling Page 44 
lbs, the fuel weight is 13,732 lbs and the payload weight is 3,869 lbs. The takeoff gross 
weight is 35,388 lbs. 
Table 12. F-16C Block 30 Combat Air Patrol Mission Weight Breakdown 
Airframe 
Empty Weight (lbs) 
Airframe Structure (lbs) 
Wing 2,096 
Fuselage 3,624 
Hor. Tail 498 
Vert. Tail 376 
Nacelles 689 
Ldg. Gear 992 
Propulsion 
System 
Engines one ~~1 
3,911 
Fuel System 578 
Fixed 
Equipment 
Hydraulics & Pneumatics 311 
Electrical 686 
Avionics 2,438 
mstrumentation 107 
De-ice & A/C 267 
Aux. Gear 172 
Furnish & Equipment 312 
Flight Controls 730 
17,787 
Payload 
Fuel 
Drop 
Armament 20mm M-61A1 600 -
Ammunition Casings & Dram 208.5 _ 
Projectile 78.5 78.5 
Missiles (AIM9.120) xtwo 1,066 1,066 
Bombs - -
Pilot 215 -
Ext. Tanks 370 gal.x two 950 950 
300 gal. 579 579 
Pylon 172 -Payload Weight 
(lbs) 3869 2673.5 
Internal Fuselage 6,972 
External 370 x 2 gal 4,810 
300 gal 1,950 
Total Fuel (lbs) 13,732 
Takeoff Gross 35,388 
Weight (lbs) 
4.3.1. ACSYNT 
The F16C mission, as given in Figure 18, requires externally carried weapons and 
fuel. In ACSYNT the aerodynamic modeling consists of inserting appropriate values for 
the drag area, D/q, for the missiles and external fuel tanks. ACSYNT can make drag 
estimates in two ways. The first involves entering an array of drag values corresponding to 
ten different Mach numbers for each type of store. The second, which was the method 
Configuration Modeling 
employed, uses only one value of D/q for a Mach number below 0.5, and extrapolates 
using the Snodgrass method to obtain drag at higher Mach numbers. The AJM-9 missiles 
mounted on the wingtip launchers were assessed no drag penalty, as this is consider to be 
the baseline configuration. Drag for the ATM-120 missiles was obtained from the 
ACSYNT manual. Drag characteristics for the 300 and 370 gallon external fuel tanks were 
not available, and were estimated based on similarly sized external tanks in the ACSYNT 
manual. Unfortunately, the calculation of store drag is an aircraft dependent problem: the 
same missile on two different aircraft may generate different drag, as the installation may 
vary. At this point, the aerodynamics for the F-16C model have not been validated against 
polars for the real aircraft 
ACSYNT produced good agreement for overall fuel bum and mission times for the 
F16C mission. Both the total fuel burn and mission time agree to within one percent of the 
values given for the actual F -16C. Mission times and fuel burns for the F-16C are 
summarized in Table 13. When comparing the mission times per mission segment, minor 
to moderate departures from the actual times can be noticed. The first point is that although 
the mission time is less, the mission fuel bum is greater. Secondly, the estimates for the 
loiter segments are much greater, on the order of 2100 lbs, than the actual mission. And 
lastly, the estimates for the combat segment indicate that either ACSYNT's internally scaled 
turbojet engine does not accurately model the use of afterburners, or the drag values 
predicted are too low. 
Configuration Modeling Page 46 
Table 13. Mission Time/Fuel Burn Comparison 
MISSION TIME (minutes) MISSION FUEL (pounds) 
BURN 
Segment ACSYNT Actual % ACSYNT Actual % 
takeoff 7.0 7.0 0.0% 651 719 -68 -9.5% 
climb 4.3 9.9 -56.6% 702 1068 -366 -34.3% 
cruise 26.4 32.5 -18.8% 1,663 1883 -220 -11.7% 
loiter 120 120 0.0% 7,242 5775 1,467 25.4% 
combat 2.0 2.0 0.0% 697 1996 -1,299 -65,1% 
climb 3.0 6.1 -50.8% 334 447 -113 -25.3% 
cruise 31.7 32.3 -1.9% 1,143 1092 51 4.7% 
loiter 20 20 0.0% 1,441 752 689 91.6% 
Totals 214.4 229.8 1.0% 13,873 13,732 141 1.0% 
4.3.2. FLOPS 
The aircraft was modeled using FLOPS in the analysis mode. Each of the 
component weights was entered, as were the aerodynamics and engine decks. The modeler 
then simply ran FLOPS to compute the output parameters. A comparison of output with 
actual values is presented in Table 4 below. 
Table 14. Comparison of FLOPS Output to Actual Values 
Parameter FLOPS output Actual % Error 
Takeoff Weight (lb.) 34,306 35,388 -3.06% 
Empty Weight (lb.) 19,882 17,787 11.78% 
Fuel Used (lb.) 13,358 13,732 -2.72% 
Mission Time (rnin.) 212.3 229.8 -7.62% 
Wing Loading (lb./sq. ft.) 114.35 117.96 -3.06% 
The mission module in FLOPS does not have a combat segment. This problem 
was circumvented by using 360-degree turn maneuvers to simulate the two minute combat. 
Because of this, the output mission segments are not continuous. There are often jumps 
between the Mach number and altitude at the end of one mission segment and the beginning 
of the next segment. Additionally, only one descent segment is allowed per mission. 
There are no fuel penalties applied between mission segments with large altitude changes. 
For this mission, the modeler added an accelerate segment between the 2 hour loiter at 
altitude and combat at 10,000 feet to simulate descent. FLOPS does not have separate 
Configuration Modeling Page 47 
entries for maximum continuous thrust and maximum thrust with afterburner because 
transport aircraft do not use afterburners. FLOPS could not read the entire engine deck 
used to model the F110-GE-129. Altitudes and Mach numbers were removed from the 
engine deck if the F-16C would not fly at those specific conditions in the given mission. 
Results and Recommendations Page 48 
5. Results and Recommendations 
The final results will be summarized in a side-by-side comparison of ACSYNT and 
FLOPS. This comparison is based on the user surveys and the modeled configurations 
described in this report. Recall, that the modeling is based on initially non-scaled 
parameters and then a correlated configuration. As part of the future recommendations, the 
modeling of a revolutionary concept is desired. In addition, the assessment of ACSYNT 
and FLOPS used in conjunction with supporting codes is desired. Therefore, higher 
fidelity modeling is recommended. Finally, an internal examination module-by-module of 
these codes is also recommended so that the specific physics and statistical databases can be 
determined. Based on this, the ability for these codes to respond to futuristic 
configurations and technologies using existing modules can be seen. This will also include 
the ability to integrate new modules and/or use supporting codes. 
5.1, Side-by-Side Comparison 
At the completion of Phase 1 of this study, a side-by-side comparison will be 
ready. This comparison has been brainstormed by NASA personnel at Langley and Ames 
and members of the Aerospace Systems Design Laboratory at Georgia Tech. This 
comparison will utilize an assessment of the items in Table 15 and will be filled in at the 
completion of this phase. An extended description of these elements can be found in 
Appendix H. ICAD and IDAS will be evaluated at a later date. The assessment will be 
made based on the results of the user surveys and the modeling done in-house at the ASDL 
with industry data. 
Results and Recommendations 
Page 49 
Table 15. Side-by-Side Assessment 
FLOPS ACSYNT Category 
Portability 
Ease of Module Change-Out 
Optimization 
Geometric Modeling 
Customer 
Documentation 
Level of Design 
Consistency of Fidelity of Analysis 
Trends Identification 
Input 
Program Limitations 
No Fudge Rule 
Ease of Use of the Graphical User Interface (GUI) 
Readability, Traceability, and Tailorability of Source Code 
Flexibuity 
Computational Time 
Constraint and Design Variable Sensitivity 
To 
Be 
Determined 
To 
Be Determined 
Overall Rating 
5.2. Isolation vs Supporting Tools 
Recall that one of the strategies for doing trade studies is the use of supporting 
analysis in higher fidelity analysis and the use of approximate techniques (Section 1.4). 
The modeling done so far in this study is the assessment of the monolithic codes in 
isolation, with the results to be summarized to one similar to Table 15. A continuation of 
this study where the monolithic codes are used in conjunction with supporting tools is 
recommended. This type if analysis strategy is more consistent with current industrial 
practice and also is coherent with the techniques being developed for computing 
frameworks. During this study, supporting codes for each of the disciplines will be 
identified. For example, FELISA and FPS3D are two codes which can be used for 
aerodynamic analysis. The three configurations used in this initial study will be modeled 
in these supporting tools as well. Following this, another assessment similar to Table 15 
will be made. 
Results and Recommendations Page 50 
5.3. Modeling of a Revolutionary Concept 
These codes also must accommodate evolutionary as well as revolutionary 
configurations and technologies. The configurations in this initial study represent 
traditional designs. Most concepts that are modeled within these codes tend to be 
evolutions of these standard configurations. If other configurations are used, it is often the 
case that modifications to the original code must be done or parameters must be scaled past 
their region of validity. Modem day aircraft design requirements are providing these codes 
with configurations that are far outside of existing databases and technologies that are still 
developing. 
An investigation was made during the first phase of this study to determine the 
scaling laws that are realized by the codes for sizing configurations. A highly-
maneuverable fighter concept is suggested as one that will test these laws. In addition, 
such a fighter of the future will require revolutionary new technologies in order to meet the 
stringent requirements imposed on it. The modeling of this configuration, along with 
appropriate trade studies, will permit a fair assessment of the ability for new technologies to 
be integrated into the code or for information from supporting codes to be used. Again, the 
modeling of this fighter concept will truly test the claim that these monolithic codes are 
modular. 
5.4. Independent Module Evaluation 
A side-by-side comparison will be made that assess the capabilities of ACSYNT 
and FLOPS. To complement this effort, a side-by-side assessment of the individual 
disciplinary modules should also be made. This will include such things as: 
• Physics, 
• Assumptions, 
• Range of applicability, 
Results and Recommendations Page 51 
• Fidelity, and 
• Ease of generating data required for the analysis. 
This assessment can be made, in part, through the configuration modeling that was already 
done. An in-depth study of the individual modules within ACSYNT and FLOPS will be 
required. This will entail breaking apart the codes by subroutine, tracing variable flow, and 
evaluating the theory that went into the routine's development. 
This portion of the study continuation also proves to be beneficial from a 
technology advancement viewpoint. Currently, computing frameworks are providing the 
modular capabilities that will support the analysis tools of the future. This study will serve 
to provide ACSYNT and FLOPS developers the detailed information that will be required 
to transition to such a framework in the future. Future studies may involve the 
categorization of these modules into an architecture such as that shown in Figure 2 
References Page 52 
6. REFERENCES 
1. "Basic Aircraft Design (BAD) - Web," NASA Ames Research Center, 
http://fornax.arc.nasa.gov:9999/badweb/badweb.html. 
2. "ACSYNT Overview and Installation ManuaI,,, ACSYNT Institute, Virginia 
Polytechnic Institute and State University, May 1992. 
3. McCullers, L. A., "FLight Optimization System, User's Guide, Version 5.41," 
NASA Langley Research Center, December, 1993. 
4. Cathey, J., "VAX ICAD User's Guide," ASC/XRED, Obtained 1996. 
5. Maira, R., "IDAS User's Manual," Rockwell International - North American 
Aircraft, April 30, 1991. 
6. Ed. Lambert, M., Jane's: All the World's Aircraft. Jane's Information Group 
Limited, 1993-1994 
I 
i 
i 
Appendices Page 53 
APPENDICES 
Survey Page 54 
Appendix A. Survey 
FLOPS/ACSYNT 
IDAS/ICAD 
DESIGN CODE SURVEY 
Company Name 
Corporate Contact 
Code Point-of-Contact 
Page 1 of 4 
Please return by December 5, 1996 to: c/o: Dr, Dimitri Mavris; School of Aerospace Engineering, 
Georgia Institute of Technology, Atlanta Georgia 30332-0150 
Program 
Select the one code to which responses to this survey apply: ACSYNT FLOPS ICAD IDAS Version Version Version Version 
• Stand-alone • Graphical •Stand-alone • XFLOPS 
Program Ratings 
Rate this code in the following cate gories: 
Low Hi Source code easy to modify? 
I 1 3 4 5 Program logic easy to trace? 1 2 3 4 5 Confidence in program results? 1 2 3 4 5 
Easy of replacing modules? 1 2 3 4 5 
User's manual? • None 1 2 3 4 5 
Programmers manual? • None 1 2 3 4 5 
Theory manual? • None 1 2 3 4 5 
Applications manual? • None 1 2 3 4 5 
Sample input cases / examples? • None 1 2 3 4 5 
1 Verification studies? 1 2 3 4 5 
Output readability? 1 2 3 4 5 
Organization of output? 1 2 3 4 5 
Rags for plots & chart creation? 1 2 3 4 5 
Rags for extended output/debug? 1 2 3 4 5 
Adequate error warnings? 1 0 3 4 5 
f/ser Considerations 
Indicate your experience with this code; 
Level of user expertise; 
• Novice •Intermediate ^Advanced 
What is your area of expertise? 
In which disciplines are you most familiar? 
Developer Considerations 
If you are a developer, indicate the following: 
Level ot expertise: 
• Modify existing module theory 
• Integration/Architecture development 
• Graphical User Interface 
Indicate the disciplines which you are familiar with: 
• Geometry • Mission • Aerodynamics 
• Structures Q Propulsion • Performance 
• Economics • Optimization 
• Other, please specify 
Program Capabilities 
Indicate this codes' capability: 
Current operating platforms: 
• Sun • SGI • HP • RS6000 • PC • Mac 
Level of required expertise: 
• Novice • Intermediate • Advanced 
Time to create a new input deck from "scratch" 
• Minutes • Hours • Days 
Time to create a new input deck from an existing configuration 
• Minutes • Hours • Days 
Code capability: 
• Analysis • Design • Parametric Study 
Any additional comments: 
Input/Output Format and Considerations 
Rate the overall input/output of this program: 
What are the input formats feir ihis code? (Check all that apply) 
• Namelist • Fixed-Formatted • Free-Formatted 
D Interactive • Spreadsheet • Combination 
Briefly describe the files required for analysis of a "typical" 
configuration: 
Briefly describe the code output and any additional output 
capability: (i.e. post-analysis, plotting, etc.) 
What additional input/output capability do you desire or require? 
FLOPS/ACSYNT 
IDAS/ICAD 
DESIGN CODE SURVEY 
Page 2 of 4 • 
Program Modules 
Check the modules that you have worked with in this code, rate (he module characteristics, and comment nn (he capabilities and extensions, 
'••If..' '.• Raic Module 
Characteristics Low High 
Analysis equations 
developed for which class 
of vehicles? 
Comment on modeling cap abilities, consistency with current 
technologies, and module upgrades. 
• Geometry 
Fidelity; 
Ease of Input: 
Input Format: 
GUI (if available): 
Component Library: 
1 2 3 4 5 
1 2 3 4 5 
12 3 4 5 
1 2 3 4 5 
1 2 3 4 5 
• Fighter • Gen. Aviation 
• Bomber • Business Jet 
• Tiltrotor • Cargo 
• UAV Transports: 
• Missile • Low Capacity 
• Recon. • High Capacity 
• Trajectory/Mission 
Fidelity; 
Ease of Input; 
Input Format: 
Output Format; 
Mission Definition: 
1 2 3 4 5 
12 3 4 5 
12 3 4 5 
12 3 4 5 
1 2 3 4 5 
• Fighter • Gen. Aviation 
• Bomber • Business Jet 
• Tiltrotor • Cargo 
• UAV Transports: 
• Missile • Low Capacity 
• Recon. • High Capacity 
• Aerodynamics 
Fidelity: 
Ease of Input: 
Input Format; 
Output Format: 
Low Speed Aero: 
High Speed Aero: 
1 2 3 4 5 
1 2 3 4 5 
1 2 3 4 5 
1 2 3 4 5 
1 2 3 4 5 
1 2 3 4 5 
• Fighter O Gen. Aviation 
• Boraber • Business Jet 
• Tiltrotor • Cargo 
• UAV Transports: 
• Missile • Low Capacity 
• Recon. Q High Opacity 
O Structures 
Fidelity: 
Ease of Input; 
Input Format; 
Output Format: 
Weight Estimation: 
12 3 4 5 
1 2 3 4 5 
1 2 3 4 5 
1 2 3 4 5 
1 2 3 4 5 
• Fighter • Gen. Aviation 
• Bomber • Business Jet 
• Tiltrotor • Cargo 
• UAV Transports: 
• Missile • Low Capacity 
• Recon. • High Capacity 
• Propulsion 
Fidelity: 
Ease of Input: 
Input Format: 
Output Format; 
Table Lookup: 
Cycle Analysis: 
1 2 3 4 5 
1 2 3 4 5 
1 2 3 4 5 
1 2 3 4 5 
1 2 3 4 5 
12 3 4 5 
DFighter • Gen. Aviation 
• Bomber Q Business Jet 
• Tiltrotor D Cargo 
• UAV Transports: 
• Missile • Low Capacity 
• Recon. • High Capacity 
0 Performance 
Fidelity: 
Ease of Input: 
Input Format; 
Output Format: 
Size to Performance: 
1 2 3 4 5 
12 3 4 5 
1 2 3 4 5 
1 2 3 4 5 
12 3 4 5 
• Fighter • Gen. Aviation 
• Bomber • Business Jet 
• Tiltrotor • Cargo 
• UAV Transports; 
• Missile • Low Capacity 
• Recon. • High Capacity 
• Economics 
Fidelity: 
Ease of Input: 
Input Format: 
Output Format: 
Single v. Fleet LCC: 
12 3 4 5 
• Fighter • Gen. Aviation 
• Bo mber • Business Jet 
riTillmfn, HI Pornn 
1 Z J •+ j QUAV Transports: 
12 3 4 5! Q Missile • Low Capacity 
1 2 3 4 5 
12 3 4 5 
URecon. U High Capacity • Optimization 
Fidelity: 
Ease of Input: 
Input Format: 
Output Format: 
12 3 4 5 
1 2 3 4 5 
1 2 3 4 5 
1 2 3 4 5 
1 
• Fighter • Gen. Aviation 
• Bomber • Business Jet 
• Tiltrotor • Cargo 
• UAV Transports: 
• Missile • Low Capacity 
• Recon. • High Cuiacity 
FLOPS/ACSYNT 
IDAS/ICAD 
DESIGN CODE SURVEY 
Page 3 of 4 
Program Enhancements 
Indicate any additional modules that you or someone else has added: 
Module Rate Module 
Characteristics Law High 
Analysis equations 
developed for which class 
. of" vehicles? ... 
Comment on analysis and 
modeling capabilities: 
Have yen or someone else 
extended ihe capabilities of 
, jhis module? If so, explain. 
Fidelity: 
Ease of Input: 
Input Format: 
3 4 5 
3 4 5 
3 4 5 
• Fighter • Bomber 
• Transport • UAV 
• Helicopterd Missile 
Fidelity: 
Ease of Input: 
Input Format: 
12 3 4 5 
1 2 3 4 5 
12 3 4 5 
• Fighter • Bomber 
• Transport • UAV 
• HelicopterCJ Missile 
Vehicle Modeling 
Check the vehicles that you have worked with using this synthesis code, rate the ability of the code to model the vehicle type accurately for 
different studies, and describe the configurations modeled. 
Vehicle Type Rate code on Ihe ability to perform these studies Low High Which vehicles have you modeled using this code, and whai 
were.the corresponding analysis times? . 
• Fighter • Analysis 1 2 3 4 5 
• Design  2 3 4 5 
• Parametric Study 1 2 3 4 5 
• Bomber • Analysis 1 2 3 4 5 
• Design  2 3 4 5 
• Parametric Study 12 3 4 5 
• Tiltrotor 
• Propeller Driven 
• Analysis 1 2 3 4 5 
• Design  2 3 4 5 
• Parametric Study 1 2 3 4 5 
• UAV • Analysis 1 2 3 4 5 
• Design  2 3 4 5 
• Parametric Study 12 3 4 5 
• Missile • Analysis 1 2 3 4 5 
• Design  2 3 4 5 
Q Parametric Study 1 2 3 4 5 
• Recortnaisance • Analysis 12 3 4 5 
• Design  2 3 4 5 
• Parametric Study 12 3 4 5 
• General Aviation • Analysis 12 3 4 5 
• Design  2 3 4 5 
• Parametric Study 12 3 4 5 
• Business Jet • Analysis 12 3 4 5 
• Design  2 3 4 5 
• Parametric Study 12 3 4 5 
• Cargo • Analysis 1 2 3 4 5 
• Design  2 3 4 5 
• Parametric Study 12 3 4 5 
Transports: 
1 
• Analysis 1 2 3 4 5 
• Design  2 3 4 5 
• Parametric Study 12 3 4 5 
FLOPS/ACSYNT 
IDAS/ICAD 
DESIGN CODE SURVEY 
Page 4 of 4 
Code Capability/Deficiency 
Rank from I (highest) to 20 (lowest) the following categories in the areas for finther development 
Code imnrovemcnt ;ircn Kale the code on (lie need for improve [uenS in the following areas 
• Clean up coding/Remove obsolete code 
• Validation 
• Enhance Graphic User Interface 
• Simplify executive to make module integration easier. 
• Incorporate more stand-alone codes Which ones? 
• Update statistical databases Which ones? 
O improvements on existing modules 
• Visualization tools for output 
• Incorporate sensitivity analysis 
• Incorporate approximate methods 
• Incorporate probabilistic methods 
• Incorporate more optimization tools Which ones? 
• Provide translators for other codes Which ones? 
• improve documentation 
• Tutorial/Beginner's guide 
• Provide sample configurations Suggestions? 
• Standardize internal data format 
• Ease of preparing input 
• Standardize output data format 
• Comments 
Appendix B Page 55 
Appendix B. B747-400 ACSYNT Input & Output File 
, Nov 18 96 
14:53:03 747-ACSYNT-IN 
SDATA BLOCK A 
1989 BOEING 747-400 TRANSPORT ****** 
SDATA BLOCK B 
1,1 
SDATA BLOCK C 
5,10, ,5 
SDATA BLOCK D 
.05,.02,,.001 
SDATA BLOCK E 
1,570,-1 
SDATA BLOCK F 
1.8,5., 
SDATA BLOCK G 
1, 60,1. 
SDATA BLOCK H 
1 
SDATA BLOCK I 
581,581,1 
30.,,90., 
SDATA BLOCK V 
END 
TRANSPORT 
5 4 5 570 585 0 0 
.0002 .6 10E8 
1 2 3 4 6 
12 6 
1 3 4 2 6 
***** GEOMETRY FOR BOEING 747-400 *** 
SWING SWEEP=37.5,KSWEEP=1,TAP£R=0.1752,TCROOT=0.1344,TCTIP= 
ZROOT=-01.0,DIHED=7,0,AREA = 5814.,AR = 7,688, WFFRAC-.80, 
XWING=0.45, SEND 
SHTAIL SWEEP=41.0,KSWEEP=1,AR=3.44,TAPER=0.27,TCROOT=0.11,TCTIP=0, 
ZROOT=0.69,AREA=1470.O,SIZIT=F,XHTAIL=0.84, SEND 
SVTAIL SWEEP=41.O,KSWEEP=1,AR=1.23,TAPER=0.29,TCROOT=0.11,TCTIP=0.09, 
ZROOT=0.6,AREA=830,0,SIZIT=F, SEND 
SFUS FRN=2.5,FRAB=3.5,WALL=0.4,DRADAR=2.0,LRADAR=2,0,BODL=225.2 , 
BDMAX=20.2, ITAIL=1, SEND 
SCREW NCREW=2, SEND 
SENGINE N=4, SEND 
S EL-EC LENGTH= 3.0, $ END 
SPASS NFIRST=34, NCOACH=378, SEATWC=20. 
SWPOD 
=0.08, 
09, 
SEND 
LENGTH 
Z 
LENGTH 
Z 
15.000, 
-0.830, 
15.000, 
-0.830, 
X 
SWFACT 
X 
SWFACT 
0.631, 
1.000, 
0.631, 
1.000, 
DIAM 
Y 
SEND 
SWPOD 
DIAM 
Y 
SEND 
SSS$$S$$$$S$$$S$$$$SSSS$$$$SS$SSSS$$$$$SSS$$S$$$SSSSS$S$SSSSS$$$SS$SSSS$$ 
STRDATA 
FRFURE=0.06, 
XDESC=100.O, 
MMPROP=L, 
NMISS = 2, 
TIMTOL=30 
WFEXT=0.0 
IPST01=5, 
LEGRES=3 , 
SEND 
9 
8.000, 
0.241, 
6.200, 
0.441, 
TIMTO2=0.5, 
WFTRAP=0.0, 
IPST02-2, 
IBREG = 0, 
RANGE=3 800,0 , 
CRMACH=.85, 
IP£IZE=0, 
QMAX=400., 
NLEGCR=30, 
NLEGCL-20, 
96000. 
MACH NO. ALTITUDE HORIZONTAL 
CLIMB 0 .00 0. 85 -1 35000 0 .0 O.C 0.0 250 0 1.0000 1 3 -1 0 0 0 0 
CRUISE 0 . 85 0 . 85 -1 -1 250.0 0.0 0.0 0 3 1.0000 1 •i 0 0 0 0 3 
LOITER 0 .30 0,30 1500 1500 0.0 30.0 0.0 0 0 1.0000 1 4 0 0 0 0 0 
9 96000. 
MACH NO. ALTITUDE HORIZONTAL NO. VTND 
PHASE START END START END DIST TIME TURN "G" S WKFUBL M IP IX W B A P 
CLIME 0 .42 O.OO 0 10000 0.0 0.0 O.O 250 0 1.0000 1 2 -1 0 0 0 0 
ACCEL -1 0.51 LOOOA 100O0 0.0 0.0 0.0 0. 0 1.0000 1 2 -1 0 0 0 0 
CLIMB 0 .42 0.00 -L 33000 0.0 0.0 0.0 270. 0 1.0000 1 2 -1 0 0 0 0 
CRUISE 0 ,85 O.OC -I 40000 1800.0 O.C 0.0 0. D 1.0000 1 4 0 0 0 0 0 
CRUISE 0 .85 0.00 -L 40000 3000.0 0.0 0.0 0 0 1.0000 1 1 -1 0 0 0 0 
DESCENT 0 .85 0. 00 -L 0 0.0 0.0 0.0 0 0 1.0000 1 5 0 0 0 0 0 
CLIMB 0 .00 0 .85 -I 350OC 0.0 0.0 0.0 250 0 I .OOOO 1 3 -1 C 0 0 0 
CRUISE 0 . 85 0 .85 -L -1 250.0 0.0 0.0 0 C 1.0000 1 4 0 0 0 0 C 
LOITER A ,30 0.30 1500 1500 0.0 30.C 0.0 0. 0 1.0000 1 4 0 0 0 0 0 
***** AERODYNAMICS OF THE BOEING 747-400 **** * 
SACHAR ABOSE = 0 .18 ALMAX=20.0, AMC=40 .0, BDNOSE= 0.0, BTEF=0.00, 
CLO=0.000,0.000,0.000,0.000,0.000,0.000,0.000,0.000,0.000,0.000, 
CLOC=0.000,0.000,0.000,0,000,O.000,0.000,0.000,0.000,0.000, 0.000, 
86,0.87,0.89,0.91, 
XCDC=0.60, XCDW=0. 
0, 0.0, 0.0, 0.0, 
FCDL=1.0, 
, FENG=1.000, 
.000, FMDR=1 
PHASE START END START END DIST TIME TURN "G S WKFUEL M IP IX W B A p ICDO=0, SEND 
SATAKE CLLAND=-1.00, CLT0=-1.00, DELFLD=45.0 , DELFTO=45.0, 
CLIMB 0.42 0.00 0 10000 0.0 0.0 0.0 250 0 1.0000 1 2 -1 0 C 0 0 DELLED=30.0, DELLTO=30.0, LDLAND=-1.0, LDTO=-1.0, SEND 
ACCEL -1 0.51 10000 10000 0.0 0.0 0.0 0 0 1.0000 1 2 -1 0 0 0 0 SAPRINT ECHOIN=L, ECHOUT=0, INTM=0, IPBLNT=0, IPCANSO, IPENG=0, IPEXT=0, 
CLIMB 0.42 0.00 -1 33000 0.0 0.0 0.0 270 0 1,0000 1 2 -1 0 0 0 0 IPFLAP=0, IPFRIC=0, IPINTF=0, IPLIFT=0, IPMIN=0, IPWAVE=0, KERROR 
CRUISE 0.B5 0.00 -1 40000 2230.0 0.0 0.0 0 0 1.0000 1 4 0 C 0 0 0 SEND 
CRUISE 0.85 0.00 -1 40000 5000.0 O.O 0.0 0 0 1.0000 1 4 -1 0 0 0 0 ***** GENERAL ELECTRIC CF6-80C2 TURBOFAN ***** 
DESCENT 0.85 0.00 -1 0 0.0 0.0 O.C 0 0 I.OOOO 1 5 0 0 0 0 0 5 
CLOW=0.00,0.00,0.00,0.00,0.00,0.00,0.00,0.00,0.00,0 
CMO=0.000,0.000,0.000,0.000,0.000,0.000,0.000,0.OOC 
RALOIT= 0.00, RCLMAX=1.000, 
ROC=.05, ROCAN=.020, SFWF=1.00, 
SMNSWP=0.10,0.76,0.80, 0.82, 0.84,0.85,0 
SPANAC= 0.0, SWPMAX=6O.0, SWPMIN= 0.0, 
YSWP= O.O, 0.0, 0.0, 0.0, 0.0, 0.0, 0 
AJCAN=0, ALELJ=5, INORM=L, ISMNDR=0, 
ISUPCR=0, ITRAP=0, IXCD=1, 
ELLIPC=F, ELLIPH=F, ELLIPW=F, $END 
SAMULT CSF=1.000, ESSF=1.000, FCD=1.00, FCDF=1.00 
FCDRA=10*1.0, 
PCDO=1.0, FCDW=0.600, FCDWB=1.000 
FLBCOR=L.000, FLD=1.000, FLECOR=L 
SATRIM CAND= 0.0, CFLAP=10.00, CGM=0.25, 
FLDM= 10*1.09, 
FVCAM=10*1.OO, 
IT= 0.0, SFLAP= 950.0, SM=0.20, 
SPANFS 95,0, ZCG= O.O, 
ITRIM=10*1, IVCAM=1, SEND 
ALIN= 0.,.5,1.0,2.0,3.0,4.0,5.0,5.5,6.0,7.0, 
ALTV= 6*25000.0,3S000.,40000., 
CLINPT=0.0,0.0,0.0,0.0,0.0,0.0,0.0,0.0,0.0,0 
SMN=0.70,0.76,0.80,0.82,0.84, 0.85,0.85, 0.85, 
ICOD=L, IPLOT=L, 
0,0,0,0,0, 
0,0,0,0, 
0,0,0,0, 
, SEND 
O.OO, O.OO, 
O.OO, O.OO 
0.00, 0.00, 
O.OO, 0.00, 
0.0, 0.0, 0 
OO, 
0.000,0 OOO, 
60, 
FINTF=O.700, 
045, SEND 
SADET 
IALF=0, IALP=2, 
ISTRS=0,0,0,0,0 
ITB=O,0,0,0,0,0 
ITS=0,0,0,0,0,0 
NALF=10, NMDTL= 
SADRAG CDBMB= 0.00, 
CDONPT= 0.00 
CDSTR= 0.00, 
CDTNK= 0.00, 
CDEXTR= 0.0, 
SMNCDO-0.00,0.00 
SMNBMB=0.00,0.20 
SMSTRS=O.00,0.20 
SMTANK=0.00,0.20 
SMEXTR=0.00, 0.20 
0.00, 
, 0.00 
O.OO, 
O.OO, 
,O, O.O 
O.OO, O.OO, 
0.00, 0.00, 
0.00, 0.00, 
0.00, 0.00, 
0.0, 0.0, 
O .OO, 
0 . 00 
0.00, 
0 .00, 
O.O, 
O.OO, O.OO, 
O.OO, O.OO 
0,00, 0.00, 
0,00, 0.00, 
0.0, 0.0, 
00, 
0.00, 
O.OO, 
0 .00, 
0 .00, 
0.00,0.00,0.00,0.00,0.00,0.00,0.00,0 
0.40,0.60,0.80,1.00,1.20,1.40,1.60,1.80, 
0.40,0.60,0.80,1.00,1.20,1.40,1.60,1.80, 
0.40,0.60,0.80,1.00,1.20,1.40,1.60,1.80, 
0.40,0.60,0.80,1.00,1.20,1.40,1.60,1.80, 
Nov 18 96 14:53:03 
SLEWIS TWTO=.266, 
BA = 7.00, 
ETAF1=.92S, 
DIA1=7.75, 
747-ACSYNT-IN 
YREN = 84. 
P11P1=2.12 
ETAC1 = .9 
SFINSP-1.0 
XMACH-0.0,0.75, 0.775,0 
NEWINL = 1 
OO, SODG = 4 . , 
MINPR=0, 
SFBTP =0 
SEND 
$ INLET 
INTYPE=1, LM=1 
SEND 
SAFTSD 
SEND 
TRANSPORT 
747-400 WEIGHTS ** 
PRFD=1.62, P2P1-30.4, SCPR= 
0, ETAT1=.93, EB1=.95, T3 = 
NDTAIL=6, RLENG = 1,2, 
B, 0.82S,0.85,ALTD=0.,5*35000.0, 
SFDIVP=0.20. SFIP = 0.20, 
1 .21, 
2800., 
SFPRFP =0.0, 
>PTS ITAIL=1, WGTO=870000. , 
SLOPE!1) = 1 150, SLOPE(2) = 1 360, SLOPE(19) « 1 250, 
SLOPE;3) 1 000, SL0PE(4) 1 075, SLOPE(5) = 0 800, 
SLOPE(6) 1 000, SLOPE(7) = 1 000, SLOPE(8) = 1 360, 
SLOPE(9) 1 056. SLOPE(10) = 1 056, 
SLOPE(ll) = 
1 056, 
SLOPEU2) = 1 055, SLOPE(13) = 1 056, SLOPE(14) = 1 056. 
SLOPE(15) = 1 056, SL0PEU6) = 1 056, SLOPE(171 = 1 056, 
AFMACH 2 400, KWING = 2, KBODY 2, 
ITHRV 4, ITAIL 0, AFMACH .90, 
WBPPAS 40. , WPPAS = 168 , WCPPAS 50 
SEND 
SFIXW WCARGO=10307., SEND 
Nov 18% 
15:07:47 j 
CCCCCCC 0000000 PPPPPPP EEEEEEE 
C 0 0 P E E 
C 0 0 P P E 
C 0 0 PPPPPPP EEEE 
C 0 0 P E 
C 0 0 P E 
CCCCCCC OOOOOOO P EEEEEEE 
CONTROL PROGRAM 
FOR 
ENGINEERING SYNTHE 
TITLE 
1989 BOEING 747-400 TRANSPORT **«*«* 
CARD IMAGES OF CONTROL DATA 
'ARD IMAGE 
1) $T) AT A BLOCK A 
2) 1989 BOEING 747-400 TRANSPORT *** 
3} $DATA BLOCK B 
4) 1,1 
4) 1 1 
5) SDATA BLOCK C 
6) 5,10, ,5 
6) 5 10 
7) $DATA BLOCK D 
8) -05,.02,,.001 
8) ,05 ,02 
91 
9) 
10) SDATA BLOCK E 
11) 1,570,-1 
747-ACSYNT-OUT 
ID 570 
12) SDATA BLOCK F 
13) 1.8,5., 
13) 1.8 5, 
14) SDATA BLOCK G 
15) 1,60,1. 
15) 1 60 1. 
16) SDATA BLOCK H 
17) 1 
17) 1 
18) SDATA BLOCK 1 
19) 581,531,1 
19) 581 581 1 
20) 30.,,90., 
20) 30. 90, 
21) SDATA BLOCK V 
22) END 
TITLE: 
1989 BOEING 747-400 TRANSPORT ****** 
CONTROL PARAMETERS; 
CALCULATION CONTROL, NCALC = 1 
NUMBER OF GLOBAL DESIGN VARIABLES, NDV = 1 
NUMBER OF SENSITIVITY VARIABLES, NSV = 0 
NUMBER OF FUNCTIONS IN TWO-SPACE, N2VAR = 0 
NUMBER OF APPROXIMATING VAR. NXAPRX = 0 
INPUT INFORMATION PRINT CODE, IPNPUT = C 
DEBUG PRINT CODE, IPDBG = 0 
CALCULATION CONTROL, NCALC 
VALUE MEANING 
1 SINGLE ANALYSIS 
I OPTIMIZATION 
3 SENSITIVITY 
4 TWO-VARIABLE FUNCTION SPACE 
5 OPTIMUM SENSITIVITY 
6 APPROXIMATE OPTIMIZATION 
* * OPTIMIZATION INFORMATION 
GLOBAL VARIABLE NUMBER OF OBJECTIVE = 570 
MULTIPLIER (NEGATIVE INDICATES MINIMIZATION) = -.1000E-O1 
CONMIN PARAMETERS (IF ZERO, CONMIN DEFAULT WILL OVER-RIDE) 
747-ACSYNT-OUT 
I PRIM': FTMAK IQTDIR NSCAT 
. ) 
IOOOOE-O: 
.AAAOOETOO 
] •: FUN 
. DDFLDOK-TOO 
FDCELM 
.200006-01 
CTLKIH 
. 00000E*OO 
DAB:- : I 
.DOOJOE+00 
ITRM LIKOBJ MACRT^L 
0 3 
CT 
NFDG 
0 
. OOOOOETOO 
THETA 
.0D00OE+O0 
ALPHAX 
.OOFLNRJEFOO 
CTMIN 
.10RJ0.GS-02 
PHI 
.0000(1)'.! 00 
ABOBJ1 
.OOOOOETOD 
PFCSIGN VARIABLE INFORMATION 
NCN-ZPFLO IHLTTAL VALUE WILL OVES RIDE MODULE INPUT 
D. V. LOWEK 
NO. BOUND 
1 . 180QOE+01 
DESIGN VARIABLES 
D. V. GLOBAL 
ID NO. VAR. HO. 
1 1 60 
BOUND 
. 500003+01 
MULTIPLYING 
FACTOR 
.10CG0E+01 
INITIAL 
VALUE 
. OOD0OE+00 
SCALE 
-OOO00E+O0 
C0N9TJU INT INFORMATICS 
THERE ARE 1 CONSTRAINT SETS 
GLOBAL GLOBAL I.JKKAR LOWER 
RMALISAI)ON 
10 VAR, 1 VAR. 2 ID BOUND 
FACTOR 
1 5BT. 581 1 .30000E+02 
. 900002I02 
TOTAL NUMBER OF CONSTRAINED PARAMETERS = 
NORMALIZATION 
FACTOR 
-3(JQ00FR*02 
CMS NO 
BOUND 
. 90000E+02 
* ESTIMATED DATA STORAGE REQUIREMENTS 
INPUT' EXECUTION 
) 9 19 
AVAILABLE 
5000 
INTEGER 
EX?: :v\ ION AVAILABLE 
1000 
NLIKBRR MODULE 
AAAAAAA CCCCCCC S55SSSE V Y N N 1 R.LKTRY 
A A C a Y Y WN N T 2 TRAJECTORY 
A A C s Y Y UN N T 3 AERODYNAMICS 
AAAAAAA C SS3SSSS Y N N M T 4 PSI'LPUI.PTON 
A A C S Y N N N T 5 STABILITY AND CONTROL 
A A C S Y N N T 6 WEIGHTS 
A A ccccccc SSSS3SS Y N N R 8 
9 
11 
14 
SONIC BOOM 
ECONOMICS 
SUMMARY OUTPUT 
TAKEOFF AND LANDING 
FOR 
AIRCRAFT SYNTH ]'•: SIS 
A a E S PRO 
TITLE 
1989 BOEING 747-400 TRANSPORT **'* 
AIRCRAFT TYPE - TRANSPORT 
1 TITLE: 
19S5 BOEING 747-400 TRANSPORT *** 
AIRCRAFT TYPE - TRANSPORT 
CONTROL PAHAJIETEKS : 
READ CONTROL, BREAD = 
EXECUTION CONTROL, SESEC = 
WHITE CONTROL, MWLII'TE = 
NUTFBER IDENTIFYING CONVKRGKJJCE 
VARIABLE FOR CONVERGED VEHICLE. I'JBJ -
NUMBER IDENTIFYING COMPARISON 
VJUTLASNE FOR CONVERGED VEHICLE, JC-BJ -
SUMMARY OTRRROR PRINT COPE, IPSUM = 
GTOBAL ERROR PRINT CODE, KGLOBP -
GLOBAL COMMON INITIALIZATION CODE, I.N IT = 
DEBUG PRINT CODF,, IPDBG = 
GLOBAL PLOT CONTROL, IGFLT = 
DATA TRANSFER INFORMATION FILE, IRCDTR 
DATA TRANSFER INFORMATION PRINT, 1FDTR 
VEHICE CONVERGENCE INFORHATIQMJ 
CONVERGENCE TOLERANCE, TUL - .2O000EO3 
ESTIM WCALC VS WEXT SLOPE = .60O«.°'K+UO 
BOUKE'ING WEIGHT, WGHAX = .100D&E+08 
MODULE IDENTIFICATION NUMBERS: 
5 
4 
5 
570 
585 
0 
0 
0 2 1 1 
C 
KCWI • ARE 
1 2 
"ALL ED FOP. EH PUT IN THE POFCLOWTHG OKDEB 
3 4 i 
Nov 18 96 
15:07:47 747-ACSYNT-OUT 
00 00 OC 
2 53 1 76 9 76 
MODULES ARE CALLED FOR EXECUTION IN THE FOLLOWING ORDER; 5 05 2 91 26 54 
12 6 0 7 58 3 86 46 85 
10 10 4 69 69 22 
12 62 5 43 92 14 
MODULES ARE CALLED FOR OUTPUT IN THE FOLLOWING ORDER: 15 15 6 10 116 72 
1 3 4 2 6 17 67 6 69 140 64 
20 20 7 23 164 08 
22 73 7 71 186 68 
25 25 8 14 208 15 
INPUT £OR MODULE # 1 27 78 8 52 228 24 
* *********** 30 3C 8 86 246 72 
32 83 9 16 263 43 
GEOMETRY INPUT DATA 35 35 9 41 278 20 
I »**». GEOMETRY FOR BOEING 747-400 ***** 37 88 9 62 290 90 
40 40 9 30 301 44 
2 SWING SWEEP=37.5,KSWEEP=1,TAPER=0.1752,TCR00T=0.1344,TCTIP=0.08, 42 93 9 93 309 72 
4S 4B 10 02 315 68 
3 ZROOT=-01.0,DIHED=7.0,AREA = 5814.,AR = 7.688, WFFRAC=.80, 47 97 10 08 319 27 
50 50 10 10 320 47 
4 XWING=0,45, SEND 60 90 10 10 320 47 
71 30 10 10 320 47 
5 SHTAIL SWEEP=41.0,KSWEEP=1,AR=3.44,TAPER=0.27,TCROOT=0.11,TCTIP= 0 .09, 81 70 10 10 320 47 
92 10 10 10 320 47 
6 ZROOT=0.69,AR£A=1470.0,SIZIT=F,XHTAIL-0.84, SEND 102 50 10 10 320 47 
112 90 10 10 320 47 
7 SVTAIL SWE£P=41.0,KSWEEP=1, AR=1.23,TAPER=0.29,TCROOT=0.11,TCTIP= 0 .09, 123 30 10 10 320 47 
133 70 10 10 320 47 
8 ZROOT=0.6,AREA=830.0,SIZIT-F, SEND 144 10 10 10 320 47 
154 5C 10 10 320 47 
9 SFUS FRN=2.5,FRAB=3.5,WALL=0.4,DRADAR=2.0,LRADAR=2.0,BODL=225.2, 158 03 10 08 319 27 
161 57 10 02 315 68 
10 BDMAX=20.2, ITAIL=1, SEND 165 10 9 93 309 72 
11 SCREW NCREW=2, SEND 
168 
172 
64 
17 
9 
9 
80 
62 
301 
290 
44 
90 
175 71 9 41 278 20 
12 $ENGINE N=4, SEND 179 24 9 16 263 43 
182 78 8 86 246 72 
13 SELEC LENGTH=3.0, SEND 186 31 8 52 228 24 
189 85 8 14 208 15 
14 $PASS NFIRST=34, NCOACH=378, SEATWC=20.0, SEND 193 38 7 71 186 68 
196 92 7 23 164 08 
15 SWPOD 200 46 6 69 140 64 
203 99 6 10 116 72 
16 DIAM = 8.000, LENGTH = 15.000, X 0 . 631, 207 52 5 43 92 14 
211 06 & 69 69 22 
17 Y - 0.241, Z = -0.830, SWFACT = 1 .000, 214 60 3 86 46 85 
218 13 2 91 26 54 
18 SEND 221 
225 
66 
20 
1 76 
00 
9 76 
00 
19 SWPOD 
21 
22 
DIAM 
SEND 
6.200, LENGTH 
0.441, Z 
15.000, X 
-0.830, SWFACT 
631, 
000, 
MAX. DIAMETER.. 
FINENESS RATIO. 
SURFACE AREA... 
VOLUME, 
FUSELAGE 
20.200 
11,149 
. 12180.937 
. 56207.191 
END OF GEOMETRY DATA CARDS 
22 LINES READ 
GEOMETRY INITIAL OUTPUT 
FUSELAGE DEFINITION 
X R AREA 
GEOMETRY INITIAL OUTPUT 
DIMENSIONS OF PLANAR SURFACES (EACH) 
WING H.TAIL V.TAIL CANARD UNITS 
NUMBER OF SURFACES. 1.0 1.0 1.0 
PLAN AREA 5814.0 1470.0 830.0 
SURFACE AREA 11694.6 2069.8 1072.9 
VOLUME 15392.0 2442.9 1717.0 
(SQ.FT.) 
(SQ. FT . ) 
(CU.FT.) 
Nov U96 
J5.07.47 747-ACSYNT-OUT SPAN 211.419 71.111 
L.E. SWEEP 40.650 46.024 C/4 SWEEP 37.500 41.000 T.E. SWEEP 26.264 20.204 ASPECT RATIO 7.688 3,440 
ROOT CHORD 46.800 32.554 ROOT THICKNESS 75.480 42.971 ROOT T/C . 134 .110 TIP CHORD 8.199 8.790 
TIP THICKNESS 7.871 9.493 TIP T/C . 080 .090 TAPER RATIO .175 .270 MEAN AERO CHORD... . 32.015 22.949 
LE ROOT AT 89.640 193.721 C/4 ROOT AT 101.340 201,859 TE ROOT AT 136.440 226.275 LE M.A.C. AT 124.405 208.615 
C/4 M.A.C. AT 132.409 214.352 TE M.A.C. AT 156.420 231.564 Y M.A.C. AT 40.490 14.372 LE TIP AT 180.404 230.570 
C/4 TIP AT 182.4S4 232,767 TE TIP AT 188.603 239.359 ELEVATION -10.100 6.969 
GEOMETRIC TOTAL VOLUME COEFF EFFECTIVE TOTAL VOLUME COEFF . 647 . 647 
31.952 47.545 41.000 11.20
1 .230 40.274 53.162 . 110 
11.680 12.614 . 090 , 290 
28.600 184.926 194.994 
225.200 199.184 206.334 227.784 
13.045 219.850 222.769 231.52
6.O60 ,050 .050 
.000 .000 (FT. ) (DEG.) ,000 (DEG,) ,000 (DEG.) 
.000 .000 (FT.| .000 (IN.) . 000 
.000 (FT. I .000 
.ooo . 000 .000 
(IN. ) (FT. ) .000 (FT.) 
.000 (FT.) .000 (FT.) ,000 (FT.) 0 (FT.) 
,000 (FT.) .000 .000 (FT.) .000 (FT.) 
.000 (FT.) (FT. ) . 000 .000 
.000 EXTENSIONS 
Strake Centroid location at .00 Area .00 Sweep Angle .0
Wetted AreaVolume .00 
Total Wing Area 5814.00 
Total Wetted Area 27018.25 
Rear Extension .00 .00 
,00 .00 
Tank Wing Fus#l Fus#2 
Total 
FUEL T Volume 7965 . 0 . 
0. 
A N K S weight 398253. 0. 
0. 398253, Mission Fuel Required = 
Available Fuel Volume in Wing 
Density 50. 00 50 .00 50 .00 
0. 
9956. 
Aircraft Weight = .000 lbs. Aircraft Volume = 75759.141 cu.ft. Aircraft Density = .000 lbs./cu.ft. 
ICASE = 4 (Fineness Ratio Method) Input for Module # 2 
********************** ****************** 
TRAJECTORY INPUT TIMTOl =30.0 TIMT02 = .5 FRFURE = .06 MENDUR = 0 . QMAX = 400. XDESC = 100.0 NCRUSE = 2 IPSIZE * 0 IPSTOl = 5 ********** IPLOT = 0 HMINP = 0. HMAXP = 40000. 
DESLF = 2,50 WKFUEL = l.ooc IPST02 = 2 DELHP = 4000. ULTLF = 3 .75 CRMACH =• .850 IBREG = 0 SMMINP .300 RANGE = 3800. WKLAND = .570 IENDUE = 0 SMMAXP = .900 WFUEL = 10000. FLFAC = ,60C I PRINT = 0 DELMP 
= .100 WFEXT 0. DECEL = .250 KERROR = 2 WCOMBP 
= 
WFTRAP 0. NLEGCL =20 NLEGCR = 30 NLEGLO = C FWGMAX = 1.200 TOL = .001 MILCOM = 0 NMISS NCODE : 2 0 MMPROP = 1 
MISSION MACH NO. ALTITUDE HORIZONTAL NO. VINO PHASE START END START END DIST TIME TURN "G"S WKFUEL M IP IX w B A P 
CLIMB .42 .00 0 10000 ,0 .0 .0 250.0 1 .0000 1 2 -1 0 0 0 0 ACCEL -1 . 51 10000 10000 .0 .0 .0 .0 1 .0000 1 2 -1 0 0 c 0 CLIMB .42 .00 -1 33000 .0 ,0 .0 270 .0 1 .0000 1 2 -1 0 0 0 0 
CRUISE .85 .00 -1 40000 2230.0 .0 .0 .0 1 .0000 1 4 0 0 0 0 CRUISE .85 , 00 -1 40000 5000.0 .0 .0 .0 1 .oooo 1 4 -1 0 0 0 0 DESCENT .85 .00 -1 0 .0 .0 .0 .0 1 .oooo I 5 0 0 0 0 0 CLIMB .00 .85 -1 35000 .0 .0 .0 250 .0 1 .0000 1 3 -1 
0 0 0 CRUISE .85 .85 -1 -1 2 50.0 . 0 .0 ,0 
1 .oooo 1 4 0 a 0 0 c LOITER ,30 . 30 1500 1500 . 0 30.0 .0 .0 
1 .oooc 1 4 0 0 0 0 
MISSION 2 (PAYLOAD = 96000. LB) PHASE MACH NO. ALTITUDE START END START END HORIZONTAL DIST TIME NO. VIND TURN "G"S WKFUEL M IP IX W B A F 
CLIMB .42 .00 0 IOOOO 0 .0 .0 250 0 1 oooo 1 to -1 0 0 0 0 ACCEL -1 .51 10000 10000 0 . 0 .0 0 1 oooo 1 2 -1 0 0 0 0 CLIMB .42 .00 -1 33000 0 .0 .0 270 c 1 oooo 1 2 -1 0 0 0 c 
CRUISE .85 ,00 -1 40000 1800 0 .0 .0 0 1 oooc 1 4 c 0 0 0 0 CRUISE ,85 .00 -1 40000 2000 0 .0 .0 0 1 oooo 1 4 -1 0 0 0 0 DESCENT .85 .00 -1 0 0 . 0 .0 0 1 oooo 1 5 0 0 0 0 0 CLIMB .00 .85 -1 35000 0 .0 .0 250 0 1 oooo 1 3 -1 c 0 0 0 
CRUISE .85 .85 -1 -1 250 0 . 0 ,0 0 1 oooo 1 4 0 0 0 LOITER .30 .30 1500 150C 0 30 .0 .0 0 1 oooo 1 4 0 0 0 0 
Input for Module # 3 
***********it**************************************** AERODYNAMIC INPUT DATA 
***** AERODYNAMICS OF THE BOEING 747-400 FACTORS FALEL = 1.000 - 25.000 FBLNT = .010 
.200 FCD = 1.000 . 900 FCDF = 1.000 
INTEGERS AND LOGICALS ALELJ = 5 NALF = 
IALF = 0 NMDTL = IALP = 2 ECHOIN = 
IAXE = 0 ECHOUT = 
10 ABOSB B ALMAX 1 AMC 
D BTEF 
REALS .180 SHK 
20.000 SM 40,000 SMNDR 
.000 SWPMA 
Novl 
15:07:47 
= 60.000 
747-ACSYNT-OUT 
FCDL = 1 OOO ICDO = 0 ELLIPC = F CGM 250 
N = 000 
FCDLH = 1 OOO RCOO = 1 ELLIPH = F CLLANE = -1 000 
= 000 
FCDO = 1 000 INORM = 1 ELLIPW = F CLTO = -1 000 
= 000 
FCDW = 600 INTM 0 CSF 1 000 
FCDWE = 1 OOO IPBLNT 0 DELFLD = 45 000 
FCL 1 000 I PENG 0 DELFTO 45 OOC 
FCLH 1 000 IPFRIC 0 DELLETJ = 30 OOO 
FDNOSE 1 OOC IPTEXT = 0 •ELLTC 30 OOO 
FENG = 1 OOC IPINTF 0 ESSF 1 OOO 
FEXF •780 IPLIFT = 0 EXA = 667 
FINTF TOO I PLOT = 1 EXC 2 000 
FLBCOR = 1 000 IPMIN 0 IT 000 
FLD 1 000 IPWAVE = 0 LDLANTJ = -1 OOO 
FLECOR 1 OOO ISMNDR = 0 LDTO = -1 OOO 
FLNOSE = 1 000 ISUPCR 0 MACHN 75C 
FLSCOR = 1 000 ITRAP = 0 QHOQ1 OOO 
FMDR = 1 045 IVCAM = 1 RCLMAX 1 OOO 
FSEP = 1 OOC IXCD 1 ROC 050 
FTRIM 1 OOO KERROR = 0 SFWF = 1 OOO 
AL1N 
7 ,000 
ALTV 
0. 
CDBME 
.0000 
CDEXTR 
.0000 
CDONPT 
.0000 
CDSTR 
.0000 
CDTNK 
.0000 
CLINPT 
.000 
CLO 
.000 
CLMIN 
,000 
CHO 
.000 
FCDRA 
1.000 
FCLRA 
1 . 000 
FLDM 
1.000 
FVCAM 
1 . 000 
ISTRS 
0 
ITB 
0 
ITS 
0 
ITRIM 
1 
SMEXTR 
1.800 
ARRAYS 
,000 
25000. 
.OOOO 
.OOOO 
.0000 
,0000 
.OOOO 
.000 
.OOO 
.000 
.OOC 
1.000 
1 .000 
1. 000 
1 .000 
0 
0 
0 
1 
.000 
.500 
25000. 
. OOOO 
.OOOO 
. OOOO 
.0000 
.OOOO 
.000 
,000 
. 000 
.000 
I.OOO 
1 . 000 
1 .000 
I.OOO 
0 
0 
0 
1 
.200 
I .OOO 
25000. 
. OOOO 
.0000 
. OOOO 
, OOOO 
.0000 
.OOO 
,000 
.000 
.000 
1 ,000 
1 . 000 
1 .000 
1 . 000 
0 
0 
0 
1 
.400 
2.000 
25000. 
.OOOC 
. OOOO 
.0000 
.0000 
.0000 
.000 
.OOO 
.000 
,000 
1 .000 
1 .000 
1.000 
1.000 
0 
0 
0 
1 
.600 
3 .000 
25000. 
.0000 
. OOOO 
.0000 
.0000 
.0000 
.000 
.000 
.000 
. 000 
1 .000 
1 .000 
I .OOO 
I .OOO 
0 
0 
0 
1 
,800 
4 .000 
25000, 
.0000 
.0000 
.0000 
.0000 
.0000 
.000 
.OOO 
.000 
.OOO 
1.000 
1.000 
1.000 
1 .000 
0 
0 
0 
1 
1 . 000 
5.000 
35000. 
,0000 
.OOOO 
.OOOO 
.OOOO 
.0000 
.000 
.000 
.000 
.000 
L .OOO 
1.000 
1.000 
1.000 
0 
0 
0 
1 
1.200 
5.500 
4000O. 
.0000 
.0000 
.0000 
.0000 
.0000 
.000 
. 000 
.000 
. 000 
1.000 
1 .000 
1.000 
l.OOC 
0 
0 
0 
1 
1.400 
6.000 
0. 
,OOOO 
.0000 
.0000 
.0000 
.0000 
.000 
.000 
,000 
.000 
1.000 
1.000 
1 . 000 
1.000 
0 
0 
0 
1 
1 .600 
SMN 
.250 
SMNBMB = 
1. 800 
SMNCDO = 
.000 
SMNSWP = 
. 910 
SMSTRS = 
1.800 
SMTANK = 
1. 80C 
YSWP 
.000 
.700 .760 .800 .820 
.000 .200 .400 .600 
.000 .000 .000 .000 
,100 .760 .800 .820 
.000 .200 .400 .600 
.000 .200 .400 ,600 
.000 .000 .000 .000 
.840 
800 1 
OOO 
.840 
800 1 
800 1 
000 
.850 
, OOC 
. 000 
,850 
.000 
,000 
OOO 
, 850 
.200 
.000 
.860 
.200 
.200 
.000 
.850 .250 
..400 1.600 
.000 
.870 
400 
400 
OOC 
.OOC 
,890 
1.600 
1.600 
.OOO 
rnpue for Module # 4 
PROPULSION INPUT 
VERSION 04-76 
GENERAL ELECTRIC CF6-80C2 TURBOFAN 
AENDIA 000 AENLE 
ALT I OOO AM 
AENTW = 000 
AUAENG = OOO AWAENG 
DELPR OOO DELTS7 
• IA1 7 750 EAfil 
EDI = 750 ETAC1 
ETAT1 c 930 HTR 
MACK1 = 1 OOO MACH2 
POSA = 29 920 PRFU 
P11P1 = 2 130 P2P1 
R32 = 940 R54 
R711 980 R711N 
SFADP 1 000 SFADSP 
SFBEP = 1 000 SFBPP 
SFDIVP = 200 SFINSP 
nlnl 4 InType 
SfSplP = 1 000 spFrfP 
Lm = 15 000 YcOYm 
theta = 10 000 psi 
lipRat 010 
SFSFC1 1 000 SFSFC2 
SMI = 500 SODG 
TR = 520 OOO TWAB 
TWTO 266 T3 
T51 = 0, T7M 
VC1 = 980 WCWA1 
XMT 850 YREN 
FRPN = OOO RDIAM 
I PR 3 I PR INT 
KERROR - 0 KODE 
KT7 0 MINPR 
N02.Z 0 NPROP 
. 000 AENWT 
. 000 ATURB 
.157 
100.000 
,750 
.900 
.300 
1.100 
1.62 0 
30.400 
.940 
,980 
1.000 
1. 000 
1.000 
1 
.000 
.900 
.000 
BA 
DEPWCC 
EB1 
ETAF1 
HVF 
PCDFAC 
PWCC 
R10A 
R54N 
SCPR 
SFAUXP 
SFBTP 
SFIP 
sf InlF 
sfWavE 
AR 
eta 
,000 
.385 
7.000 
2 . 000 
.950 
. 925 
18600.000 
1.000 
100.000 
1. 000 
. 920 
1 .210 
1 .000 
.000 
,200 
1 .000 
1.000 
1.000 
13.000 
THESE VARIABLES ARE USED BY TABLE LOOK UP 
l.OOC SFSFC3 = 1 .000 
4.000 TOSA 518.000 
0, TWOAB = 50280. 
2800. T5M 3400. 
3400. T71 0. 
.020 XMDES = 1 . 600 
84 . FRBT = .000 
1.150 RLENG = 1 .200 
0 IPLOT = 0 
2 KT5 0 
0 NAB 6 
6 NSUMM = 15 
IENG 5 
LOOK U
(CF6 ) 
747-ACSYNT-OUT 
ESF 
AL"'L) = 
XMACH = 
XMPRI * 
XPHI = 
XHPRI1 = 
.000 
XI.'TL 
.560 
XI • >R 
,ooc 
XPRI2 = 
.000 
1.000 WHTAITJ 
.ooo 
. 000 
1 .000 
. OCO 
.ACO 
. OUO 
. OOO 
, 00:5 
. 000 
. 000 
.OOO 
35000. 
.750 
. 300 
1. 000 
.ooo 
.000 
,000 
. 000 
.OOO 
. OOO 
.OOO 
.OOO 
IPDBTXI 
35C.0.U . 
.77 5 
. 60D 
1.000 
.ooo 
.OOO 
.000 
I5050. 
.800 
,900 
I. ooo 
.000 
.000 
.OOC 
.000 
35000. 
.825 
1.200 
1.000 
,000 
.000 
.OOC 
.000 
INPU" F-:-i !'ODU_U 4 F 
******* • I I +1 I I* ************ * •* 
INITIAL WEIOHTS INPUT DATA 
ACSYNT MODULE NUMBER N 
AIRCRWT 1VPE: TRANSPORT 
TITLE: ***** 747-JQ0 WEIGHTS 
0COJ1TROL OPTIONS 
I r-RINT 
IDELT 
KB 
FR =1 
STRESS = 
DPCAUIW » 
TMNTET1 M 
TECHI = 1.00 
SLOPE 11) = L.W 
SLOPE(9) - 1.06 
SLOPE US)- .00 
1)INITIAL ESTIMATES 
I.:- CODE = 1, WTUI . 
IGRAPH = 
IOBLIQ I 
00 K2 
00 K6 
00 KP1 
DO .'SCHQ = 
30000. 
5.00 IGEAR 
ITAIL = 
00 K3 
0 0 AFKACH = 
00 KP2 = 
00 WGTO 
DENS 
1 JFL'I'YP 
0 KHT 
2 KBO 
1 .0 KT 
.90 1'IAXZI 
. 00 
B70000. 
.100 
1 
OR 
Y 
0 
2 
1 . 0 
1 
:?:TGR 
1 .00 
1.36 
1 . 06 
1.25 
00 
08 
06 
.00 
. 80 
.06 
. 00 
. 00 
.06 
00 
OO 
36 
1.00 
3 5101:. 
. 850 
4 .000 
1 .000 
. 000 
. 000 
. OOO 
.000 
.OOO 
.000 
.000 
QUANTITY VALUE QUANTITY 
.000 
00 
36 
06 
L* BEGIN VEBICL* CONVERGENCE 
.'II'IK *06 ESTIMATED GROSS WEIGHT = 
Calling K<-,DULN S 1 
CALLING MODULO IF 2 
CALLING MODULE ft 6 
CALCULATES GROSS WEIGHT = .84037E+06 
SLOP^: OL Hop : VS . WEST LINE 70000E+OC 
ESTIMATED GROSS WEIG!;T 
CALHHG MODULE T I 
COLLING MODULE # 2 
CALLING MODULE # 6 
CALCULATED GROSS WEIGHT 
SLOPE OF WCALC VS. WA^T 
ESTIMATED WEIGHT 
CALLING HADIILO * 1 
COLLING MODULE 1 2 
CALLINY MODULE # 6 
CALCULATED GRTSS WEIGHT = .7 
SLOPIT OF WCA^C VS. WEST 1 IHT; 
ESTIMATED GRASS WEIGHT 
CALLING MODULO # 1 
CALLING MODULE T 2 
CULLING MODULE * 6 
CAL.ELATED GROSS WEIGHT 
. 77122E + 06 
.77808E+06 
LINE = .6305SHOC 
.78978E+06 
1-06 
. 61484E+O0 
. 78SS2E+06 
. 7S884E+06 
** END VEHICLE CONVERGENCE ** 
3 CONVERGENCE ITERATIONS REQUIRED 
CNLLIDSJ MODULE K 
CALLING MODULE * 
CALLING MODULU # 
OUTPUT FOR MODUI 
WAF 261000. 0 
WAPO 348 . 0 
WARM = 0 , 0 
WBB2 = 0. 0 
WCAKD 0. 0 
WCREW = 6090. 0 
WELT = 7 81 3 . A 
WIITANX - A. 0 
WFS » 6090 . 0 
WG EAR = V 0 
WHT 6960 . 0 
WLG 43500. 0 
WNA 8700 . 0 
WPA^S I3050D. 0 
WP? - 696HJ0. 0 
WTSI1H 870000, 0 
6960.J. 0 
W: JV = 0. 0 
W[,IFTF C C 
WTUFLV 119FC2. 0 
WA1RC = 8700 . 0 
WAMMIJN = Q 0 
WBAG -- 26100. G 
WHOI.1Y 1041DD. LJ 
WCARGO - 10307. ] 
WE - 52200• 0 
BBS = 43IOD. 0 
WFEQ = 121300. 0 
WCA = 2*10 . 0 
WHOP 6960. 0 
WINST = 4350. 0 
WKISS 0. 0 
W PA 52200. 0 
WPL 15660*. n 
WSC * 17400. 
. T - 8700 . 0 
WBOMB = 0. 'J 
WP1V - 0. 0 
WBB2 - 0 . 0 
Nov IS 96 
15:07:47 747-ACSYNT-OUT 
FUSELAGE DEFINITION NACELLE DEFINITION NACELLE LOCATION DIMENSIONS OF PLANAR SURFACES (EACH] 
X R AREA 
00 00 00 
2 53 1 76 9 76 
5 05 2 91 26 54 
7 58 3 86 46 85 
10 10 4 69 69 22 
L2 62 5 43 92 74 
15 15 6 10 116 72 
17 67 6 69 140 64 
20 20 7 23 164 08 
22 73 7 71 186 68 
25 25 8 14 208 15 
27 78 8 52 228 24 
30 30 8 86 246 72 
32 83 9 16 263 43 
35 35 9 41 278 20 
37 88 9 62 29C 90 
40 40 9 80 301 44 
42 93 9 93 309 72 
45 45 10 02 315 68 
47 97 10 08 319 27 
50 50 10 10 320 47 
60 90 10 10 320 47 
71 30 10 10 320 47 
81 70 10 10 320 47 
92 10 10 10 320 47 
102 50 10 10 320 47 
112 90 10 10 320 47 
123 30 10 10 320 47 
133 70 10 10 320 47 
144 10 10 10 320 47 
154 50 10 10 320 47 
158 03 10 08 319 27 
161 57 10 02 315 68 
165 10 9 93 309 72 
168 64 9 80 301 44 
172 17 9 62 290 90 
175 71 9 41 278 20 
179 24 9 16 263 43 
182 78 8 86 246 72 
186 31 8 52 228 24 
189 85 8 14 208 15 
193 38 7 71 186 68 
196 92 7 23 164 08 
200 46 6 69 140 64 
203 99 6 10 116 72 
207 52 5 43 92 74 
211 06 4 69 69 22 
214 60 3 86 46 85 
218 13 2 91 26 54 
221 66 1 76 9 76 
225 20 00 00 
X-XNOSE R AREA 
.00 3 17 31.51 
2.21 3 17 31.51 
6 . 63 3 17 31. 51 
8.84 RN 17 31. 51 
X 
135.17 
135.17 
148.45 
148.45 
Y 
25 . 48 
-25.48 
46.62 
-46.62 
Z 
-12.73 
-12.73 
-12.73 
-12.73 
FUSELAGE 
MAX. DIAMETER 20.200 
FINENESS RATIO 11.149 
SURFACE AREA 12180.937 
VOLUME 56207.191 
NACELLES 
6.334 
175.906 (EACH) 
WING H.TAIL V. TAIL CANARD UNITS 
NUMBER OF SURFACES. 1.0 1,0 1.0 1. 0 
PLAN AREA 5814.C 1470.0 830.0 .0 (SQ.FT. 
SURFACE AREA 11694.6 2069.8 1072.9 .0 (SO.FT. 
VOLUME 15392.0 2442.9 1717.0 .0 (CU.FT. 
SPAN 211 .419 71 111 31 .952 .000 (FT. ) 
L.E. SWEEP 40 , 650 46 024 47 .545 .000 (DEG.) 
C/4 SWEEP 37 .500 41 ooo 41 .000 .000 [DEG.1 
T.E. SWEEP 26 .264 20 204 11 ,204 .000 (DEG. ) 
ASPECT RATIO 7 688 3 440 1 .230 .000 
ROOT CHORD 'IT . 800 32 554 40 .274 ,ooc [FT. ) 
ROOT THICKNESS 75 .480 42 971 53 .162 .ooo (IN, ) 
.134 110 , 110 .000 
TIP CHORD 8 .195 
CO 790 11 .680 ,000 (FT. ) 
TIP THICKNESS 7 871 9 493 12 .614 ,000 (IN, ) 
TIP T/C ,080 090 .090 .ooc 
TAPER RATIO .175 270 .290 ,000 
MEAN AERO CHORD.... 32 .015 22 949 28 .600 .000 (FT. | 
LE ROOT AT 89 . 640 193 721 184 ,926 .000 (FT. ) 
C/4 ROOT AT 101 .340 201 859 194 .994 .ooc IFT. ) 
TE ROOT AT 136 .440 226 275 225 .200 ,000 (FT. ) 
LE M.A.C. AT 124 .405 208 615 199 , 184 ,000 (PT. I 
C/4 M.A.C. AT 132 .409 214 352 206 .334 .000 (FT. ) 
TE M.A.C. AT 156 .420 231 564 227 .784 .000 (FT. ) 
I M.A.C. AT 40 .490 14 372 13 .045 .000 
LE TIP AT 180 ,404 230 570 219 .850 .000 (FT. ) 
C/4 TIP AT 182 .454 232 767 222 .769 .000 (FT. ! 
188 .603 239 359 231 .529 ,000 (FT. ) 
ELEVATION -10 . 100 6 969 6 .060 .000 (FT. I 
-GEOMETRIC TOTAL VOLUME COEFF 
EFFECTIVE TOTAL VOLUME COEFF 
EXTENSIONS 
, 647 
. 647 
STRAKE 
.050 
.050 
.000 
.000 
CENTROID LOCATION AT. ..... . .00 
AREA .0
SWEEP ANGLE 0
WETTED AREA .00 
VOLUME .OC 
TOTAL WING AREA 5814.00 
TOTAL WETTED AREA 27721.88 
REAR EXTENSION 
.00 
.00 
.00 
.00 
TANK 
WING 
FUS#L 
FUS#2 
TOTAL 
FUEL TANKS 
VOLUME 
7965 . 
0. 
0. 
WEIGHT DENSITY 
398253. 50.00 
0. 50.00 
0. 50.00 
398253. 
MISSION FUEL REQUIRED = 
AVAILABLE FUEL VOLUME IN WING 
335241, 
9956. 
AIRCRAFT WEIGHT 
AIRCRAFT VOLUME 
AIRCRAFT DENSITY 
= 788821.062 LBS. 
- 75759.141 CU.FT. 
10.412 LBS./CU.FT. 
ICASE = 4 (FINENESS RATIO METHOD) 
747-ACSYNT-OUT 
Detailed Aerodynamics Output 
Mach 
Altitude = 
Parasite Drag 
.25 
0. Takeoff Configuration: Flaps and Slats 
Induced Drag 
Friction .0117 Alpha CI Cd L/C Cm e Cdtrim Deltrira 
Zone 
Body .0042 0 1 038 .4856 2 1 ,000 .09 .0066 -4.7 
Wing 
T 
.0059 5 1 088 .5001 2 2 .000 .10 .0070 -4.9 
Strakes . oooo 1 0 1 137 .5145 2 2 ,000 .11 . 0074 -5.1 
H. Tail .0011 2 0 1 235 . 5428 2 3 .000 .12 .0083 -5.4 
2 
V. Tail .0005 3 0 1 331 .5705 2 3 .000 . 13 . 0091 -5.7 
canard t .0000 4 0 1 427 .5987 2 4 .000 . 14 .0099 -6.C 
6 
Interference 
.0024 5 0 1 522 . 6263 2 4 . ooo . 16 .0107 -6.3 
Wave .0000 5 5 1 569 .6400 2 5 .000 .16 .0111 -6.4 
2 
External .0000 5 0 1 616 . 6537 2 5 . 000 .17 .0114 -6.5 
Tanks .0000 7 0 1 710 .6811 2 5 . 000 . 18 . 0122 -6.7 
2 
Bombs 
Stores 
Extra 
Camber 
.0000 
.0000 
.0000 . oooo 
Cdmin 
ft 
Mach 
Altitude = 
Parasite Drag 
.25 
0 . 
Slope Factors 
Cl/Alpha (per radian) 
Cdl/Cl'2 
Alpha Transition Zone 2-
Flap Setting 
Slat Setting 
Flap Type Single 
Landing Configuration: Flaps and Slats 
Induced Drag 
5.4982 
.2282 
38 .124 
45. 
30. 
886. sq. 
Friction 
Zone 
Body 
2 
.0117 
.0042 
Alpha 
.0 1 
CI 
038 
Cd 
, 4 8S6 
L/D 
2 .1 
Cm 
,000 
e 
.09 
Cdtrim 
,0066 
Deltrim 
-4.7 
Wing 
2 
.0059 5 1 088 .5001 2 2 . OOC . 10 .0070 -4 . 9 
Strakes .0000 1 0 1 137 .5145 2 2 .ooo ,11 .0074 -5.1 
2 
H. Tail 
2 
,0011 2 0 1 235 ,5428 2 3 .000 .12 .0083 -5.4 
V. Tail 
2 
.0005 3 0 1 331 .5709 2 3 . 000 . 13 .0091 -5.7 
Canard .0000 4 0 1 427 .5987 2 4 .000 ,14 .0099 -6.0 
Interference 
2 
.0024 5 0 1 522 .6263 2 4 ,000 . 16 .0107 -6.3 
Wave 
2 
.0000 5 5 1 569 .6400 2 5 .000 . 16 .0111 -6.4 
External .0000 6 0 1 616 . 6537 2 5 .000 ,17 .0114 -6.5 
4 
Tanks 
. 0000 7 0 1 710 ,6811 2 5 , 000 . 18 .0122 -6.7 
2 
Bombs 
Stores 
Extra 
.0000 
,0000 
.0000 
Slope Factors 
Cl/Alpha (per radian) 
Cdl/Cl~2 
Alpha Transition zone 2 
5.4982 
.2282 
3 38.124 
Nov I 
15:07:47 
Camber Cdmin Et .0000 Flap Setting Slat Setting Flap Type 
747-ACSYNT-OUT 
Detailed Aerodynamics Output 
Single 
45 . 30 . 886.
 sq- Mach = .70 Altitude = 25000. 
Parasi te Drag Friction .0112 + Zone 
Body .0040 to Wing . 0056 
+ 2 
Strakes .0000 2 H. Tail .0010 
+ 2 
V. Tail .0005 2 Canard , 0000 
+ 2 
Interference .0024 + to Wave .0000 2 
External .0000 2 Tanks .oooo 
+ 2 Bombs .0000 
Stores .oooo Extra ,0000 Camber .0000 
Cdmin .0136 Mach ,76 
Altitude = 25000. Parasite Drag Friction .0111 
t Zone Body .0040 4-2 Wing .0056 
+ 2 Strakes .oooo 
+ 2 
H. Tail .0010 + 2 V. Tail .0005 
+ 2 Canard .0000 
+ 2 
Interference .0024 + 2 Wave ,0000 
+ 2 
External .oooc + 2 Tanks .0000 
+ 2 
Bombs .0000 Stores .0000 Extra ,0000 
Induced Drag 
Induced Drag 
pha CI Cd L/D Cm e Cdtrim Del trim .0 ,000 .0136 .0 .000 . 00 .0000 .0 
.5 .051 . 0137 3 . 8 .000 .79 . 0000 - .3 1.0 .102 .0141 7.3 .000 .79 .0000 -.5 
2.0 .203 .0157 12.9 , 000 .79 .0002 -1.0 3.0 .302 .0183 16.5 .000 ,79 .0004 -1.5 
4.0 .399 .0219 18.2 . 000 .79 .0007 -1.9 5.0 .495 .0264 18 .8 .000 .79 .0010 -2.3 
5.5 . 542 .0290 18.7 .000 .79 .0012 -2.5 6.0 .589 .0317 18 . 6 .000 .79 .0014 -2.7 
7.0 . 682 .0380 18.0 .000 . 79 .0018 -3.0 Slope Factors CI/Alpha (per radian! Cdl/Cl"2 
Alpha Transition 2one 2-3 programmed Flap Setting 
Flap Type Single 
5 . 5841 . 0525 12.177 0. 
886. sq. 
pha CI Cd L/D Cm e Cdtrim Deltrim ,0 .000 , 0134 .0 .000 .00 .0000 .0 
.5 .053 .0136 3.9 .000 .79 . oooo - .3 1.0 .105 .0140 7.5 .000 .79 .0001 - .6 
2.0 .208 .0157 13 .3 .000 ,79 .0002 -1.1 3.0 .310 .0185 16.8 .000 .79 .0004 -1.6 
4.0 .410 .0222 18.5 .000 .79 .0007 -2.0 5.0 ,508 .0269 18,3 .000 ,79 .0011 -2.4 
5.5 .557 , 0296 18.8 ,000 .79 .0013 -2,6 6.0 . 60S .0325 18 . 6 .000 .79 ,0015 -2.8 
7.0 .701 .0390 17.9 .000 .79 .0020 -3.2 Slope Factors Cl/Alpha (per radian) 5.7347 Cdl/C1A2 .0521 
Alpha Transition Zone 2-3 10.925 
Nov 18 96 
15:07:47 
CAMBER 
CDMIN 
FT 
. 0000 PROGRAMMED FLAP SETTING 
FLAP TYPE SINGLE 
747-ACSYNT-OUT 
0. 
386. SQ. 
DETAILED AERODYNAMICS OUTPUT 
MACH . 80 
ALTITUDE = 25000. 
PARASITE DRAG 
FRICTION .0110 
4 ZONE 
BODY .0039 
+ 2 
WING . 0055 
4 2 
STRAKES .0000 
4 TO 
H. TAIL . 0010 
4 2 
V. TAIL .0005 
4 TO 
CANARD . 0000 
4 2 
INTERFERENCE .0024 
4 2 
WAVE . 0000 
+ 2 
EXTERNAL .0000 
4 2 
TANKS .0000 
+ 2 
BOMBS .OOOO 
STORES .0000 
EXTRA .0000 
CAMBER .0000 
CDMIN .0134 
4 FT 
MACH .82 
ALTITUDE = 25000. 
PARASI TE DRAG 
FRICTION .0110 
4- ZONE 
BODY .0039 
+ 2 
WING .0055 
+ 2 
STRAKES .0000 
4 2 
H. TAIL .0010 
+ 2 
V. TAIL .0005 
4 2 
CANARD .OOOO 
T 2 
INTERFERENCE .0024 
+ 2 
WAVE . OOOO 
4 2 
EXTERNAL .0000 
4 TO 
TANKS .OOOO 
+ 2 
BOMBS .0000 
STORES .0000 
EXTRA .0000 
INDUCED DRAG 
PHA CI CD L/D CM E CDTRIM DELTRIM 
.0 .000 .0134 0 .000 .00 .0000 .0 
.054 ,0135 4 0 .OOO . 80 . 0000 -.3 
1.0 .107 .0140 7 7 . 000 .80 .0001 - . 6 
2.0 .213 ,0157 13 5 ,000 .80 ,0002 -1.1 
3.0 .316 .0186 17 0 .000 .80 .0005 -1. 6 
4.0 ,418 .0225 18 6 .000 .80 .OOOA -2 .1 
5.0 . 519 .0273 19 0 .000 . 80 . 0012 -2.5 
5.5 .568 .0301 18 9 .OOC .80 .0014 -2.8 
6.0 .617 .0332 18 6 .000 .80 .0016 -3.0 
7.0 ,715 .0399 17 9 . 000 .80 .0021 -3.3 
INDUCED DRAG 
SLOPE FACTORS 
CL/ALPHA (PER RADIANL 
CDL/CL~2 
ALPHA TRANSITION ZONE 2-3 
PROGRAMMED FLAP SETTING 
5,8517 
.051S 
10.177 
0 , 
FLAP TYPE SINGLE 
PHA CI CD L/D CM E CDTRIM DELTRIM 
.0 . 000 ,0134 0 ,000 . 00 .0000 .0 
. 5 .054 . 0135 4 0 ,000 . 80 ,0000 -.3 
1.0 .108 .0140 1 8 .000 .80 .0001 - . 6 
2.0 ,215 ,0158 13 6 .000 .80 .0002 -1.2 
3.0 .320 . 0187 17 1 .000 . 80 .0005 -1.7 
4.0 , 423 .0226 18 7 .000 .80 .0008 -2.2 
5.0 .524 , 0276 19 0 .000 ,80 .0012 -2.6 
3.5 .574 ,0304 18 9 .000 .80 .0014 -2.8 
6.0 . 624 .0335 18 6 .OOO .80 .0017 -3.0 
7.0 . 723 .0404 17 9 .000 .80 .0022 -3.4 
SLOPE FACTORS 
CL/ALPHA (PER RADIAN) 5.9162 
CDL/CL~2 .0517 
ALPHA TRANSITION ZONE 2-3 9.325 
15:07:47 
. OOOO 
FT 
. D134 
PRQ^RARAJTIED PL DP SO''TING 
FLAP TYPE SINGLE 
747-ACSYNT-OUT 
A86. SQ. 
DETAILED AERODYNAMICS OUTPUT 
AL "_I TUDE 
.$4 
250D5. 
PARASITE DR*C INDUCED DIDU 
FRICT ION 
DODY 
2 
WING 
. C 1 0G 
.0039 
A .>H:; 
. 0 
CL 
.POL' 
CJ 
.0138 
L/D 
.0 
OIL 
.000 
E 
. 00 
CDTRJJU 
.0000 
;:V.: RIM 
.0 
.0053 5 . 055 . 0140 3.9 .000 .80 .OOTTO - . 3 
STRAKES 
•> 
,0*00 1 0 . 110 .0145 7 . 6 ,000 . 80 . C • •.' - . 6 
C 
H. TAIL . 0010 2 .0 ,217 .0163 13 .4 .000 .80 . 0002 -1 .2 
V. TAIL 0005 3 0 .324 .0192 16.8 . OOO .30 , 0005 -1.7 
CANARD 
2 
. OOOO 4 0 .428 .0233 18.4 .000 . 80 .0003 -2 .2 
TJITR>RF ?R<?NCE . 0021 5 0 . 530 .0284 18 . 7 . OOO .80 . 0013 -2 . 7 
2 
WAVE . 0008 5 5 .581 .0313 18.6 .OOO . 80 .0015 -2.9 
EXTERNAL .0000 6 0 .632 .034^ 13.4 . 000 .80 ,0017 -3.1 
TANKS 
2 
. OOON 7 0 .731 .0414 17.7 . 000 .80 . 0023 -3.5 
.. S 
STORES 
EXTRA 
CAMBER 
. NOOC 
. OOOC 
.OOOO 
.0000 
SLOPE FACTORS 
CL/AIPV.,^ (PER R,.VJ.IAN) 
CDL/CL'~2 
ALPHI T^ANSI-^JN ZONE 2-
PROGIIUUUED FIN;-, SETTING 
3 
5.9B52 
.0516 
9 .486 
0. 
CDMIN . CJ 3 8 FLAP TYPE SINGLE 886. SQ. 
FT 
MACH 
ALTITUDE -
. fl 5 
25U0U, 
PARASITE DRA 
FRICTIAN 
ZONE 
]: IDY 
.0103 
.0039 
ALPHA 
.0 
DRAG 
CL 
.000 
CD 
. 0146 
L/C 
.0 
C™ 
,000 
E 
.OC 
CDCRIRJ 
. OOOO 
DELTRIM 
. 0 
2 
WING . 0055 5 ,*SS .0147 3.8 .OOC . 80 . 000 0 -.3 
STRAKES 
2 
H. TAIL 
.0000 1 0 . 110 . 0152 7.3 , 000 . 80 . 0001 - . 6 
. 0010 2 0 .219 . 0170 12.9 .000 . 80 . 0002 -1 ,2 
V. TAIL ,0005 3 0 .326 .0200 16.3 .COO .80 .0005 -1 . 7 
CANARD .0000 4 0 , 430 . 0241 17.9 . 000 . 3C , 0009 -2 . 2 
2 
INTERFERENCE 
2 
MH 5 C .53 4 .0292 18 .3 .OOC . 80 .0013 -2 . 1 
WAVE .0017 5 5 , 585 . 0322 18.2 . OOO .80 .0015 -2 . S 
EXTENII! .0000 6 0 .635 . 0354 18 .0 .000 . 80 . 0018 -3 . 1 
RANK B ,0000 7 0 .736 .0424 17 .3 .000 . 80 .0023 -3.5 
2 
BOOIIS 
STORES 
EXLCA 
.0000 
. DDDO 
£ ] NPE FJIC T ORS 
CL .'ALPHA 1 PA R R.I R:-. AN 1 
CDL/CL-2 
6.0216 
.051B 
ALPHA TRAJIAISIPN ZONE 
Nov IS % 
J 5:07,47 
Camber 
Cdmin 
ft 
.oooo 
.0146 
Programmed Flap Setting 
Flap Type Single 
747-ACSYNT-OUT 
0. 
886 . Mach = . B5 
Altitude = 35000. 
Parasite Drag 
Friction .0109 
+ Zone 
Body .0039 
+ 2 
Wing .0055 
4 2 
Strakes ,0000 
4 2 
H. Tall .0010 
+ 2 
V. Tail .0005 
4 CO 
Canard .0000 
4 TO 
Interference .0019 
+ 2 
Wave .OON 
4 2 
External .0000 
4 2 
Tanks .0000 
4 2 
Bombs .OOOO 
Stores .OOOO 
Extra .OOOO 
Camber .0000 
Cdmin .0146 
* ft 
Mach . 85 
Altitude = 40000. 
Parasite Drag 
Friction .0109 
4 Zone 
Body .0039 
4 2 
Wing .0055 
4 TO 
Strakes .OOOO 
4 2 
H. Tail . 0010 
4 2 
v. Tail .0005 
4 2 
Canard .0000 
4 2 
Interference ,0019 
4 2 
Wave .0017 
4 2 
External .OOOO 
4 2 
Tanks .0000 
4 CN 
Bombs .0000 
Stores .0000 
Extra OOOO 
Induced Drag 
Alpha CI 
.0 
, 5 
1 .0 
2.0 
3.0 
4 . 0 
5.0 
5.5 
6.0 
7 .0 
.000 
.055 
.110 
.219 
.326 
. 430 
.534 
. 585 
. 635 
.73 6 
Induced Drag 
Cd 
.0146 
,0147 
.0152 
L/D 
.0 
3 .8 
7.3 
.0170 12.9 
.0200 16.3 
.0241 17.9 
.0292 18.3 
.0322 18.2 
.0354 18.0 
.0424 17.3 
Cm 
,000 
.000 
.000 
,000 
.000 
.000 
.000 
.000 
.000 
.000 
e Cdtrim Deltrim 
.00 
.80 
,80 
.80 
.80 
.80 
.80 
.80 
.80 
.80 
.0000 
.0000 
.0001 
,0002 
.0005 
.0009 
.0013 
.0015 
.0018 
.0023 
. 0 
-.3 
-.6 
-1.2 
-1.7 
-2,2 
-2 .7 
-2.9 
-3.1 
-3.5 
Slope Factors 
Cl/Alpha (per radian) 
Cdl/Cl"2 
Alpha Transition Zone 2-3 
Programmed Flap Setting 
Flap Type Single 
6.0216 
.0515 
9.321 
0. 
886. sq. 
pha CI Cd L/D Cm e Cdtrim Del trim 
.0 .000 ,0146 . 0 . 000 .00 .0000 .0 
. 5 .055 , 0147 3 . 8 .000 .80 . OOOO - .3 
1.0 .110 .0152 7.3 .000 .80 .0001 -.6 
2 . 0 .219 .0170 12 . 9 , 000 .80 .0002 -1 .2 
3.0 .326 .0200 16 .3 .000 .80 .0005 -1.7 
4.0 ,430 ,0241 17.9 .000 .80 .0009 -2.2 
5.0 . 534 . 0292 18.3 . 000 ,80 . 0013 -2.7 
5.5 .585 ,0322 18.2 .OOO .80 ,0015 -2 .9 
6.0 . 635 .0354 18. 0 .000 .30 .0018 -3 .1 
7.0 .736 .0424 17 .3 .000 . 80 .0023 -3.5 
Slope Factors 
Cl/Alpha (per radian) 6.0216 
Cdl/Cl"2 .0515 
Alpha Transition Zone 2-3 9.321 
Detailed Aerodynamics Output 
Nov 18 % 15:07:47 747-ACSYNT-OUT 
CANTER .0000 PRIIGR.IMNIED. FLAP SETTING 0. 84. 853 iii . . 7B5 .716 .0005 
62. 810. 713. .857 .733 .0007 
CDNLN .CHS FLAP TYPE ,RR_:LG'I ,-• 886. SQ. 80. Si • 488. 1 .D02 - ID .0008 
• ET 7R . 93 , 2-19. 2 .949 : . 114 . 0010 
.300 35000, 100. 5O04, 505-. . 532 .530 .DOOL 
OUTPUT £OR KC-CIULE * 4 98. 4387. 4413 . .531 .524 .0002 
SC. 3774- 3402 . .53. .532 .1 >U2 
L ENF IKK S'JMMAFY ••• 315C. 3188 . .546 . OOO 2 •2 . 
2515. 2555. .591 .532 .0002 
90. 1826. 1873 . . 6B7 . 670 .0003 
ENGIKE L) [ AMETHR 5. SI FEET 38. 1313. 1403. .77 9 .716 ,0004 
ENGINE LENGTH 7 . 37 FEET 86. 1098. 1176. .782 ,73D . 00D5 
ENGINE WEIGHT = ;• \* A. 9 5 POUNDS 84 . B52 . 551 . .S10 .726 . 0006 
IIYPAM.S RATIO - 7 . 00 32 , 603 . 726 . . 895 . :3 .OUOFL 
NO OF ENGINES 8 . :0. 34FI . 497 . 1 . 173 . 816 .0009 
•RAG REF AREA ! 00 SQ FEET •1 P. . 73 . 256. 3 .917 L . 122 , 0011 
L"WCC A PERCENT OF HNGINE CORRECTED AIRFLOW 
THRU ^T - ME T!: ( POUNDS; .»HK • ' SINE) 
SFC ™ ENGINE SPECIFIC F03L CONS .IMPTINN .825 350QO. IOO. 5053 . 5094 . ' ;r. .3J9 ,0002 
: • • L T.HTTOST PER ENGINE IH LBS. W/O INS TAL DRAG CORR 9R; 4421. 44 67 . .543 518 ,0002 
SFCU = SFC , 1 'HR, W/C INS 1' AL DRAG CORK 96 . 3802 . 38'; B . . 549 . 512 .0003 
COINS = TOT INSTALLATION DRAG COEF PEA A/C (SWING ,,•«••) '. 3175 . 3227 . ,5S<; .557 .0003 
1 92. 2529 . 25S7 . .604 .593 ,001)3 
SI 1835 19/02 . .706 .681 . 0D04 
1 348 . I03O . . EEL .7 " .(• 
•I . 10S6 . 1198 . ."->•--, .740 . DOOC 
MACH ALT PWCC THR'J.ST TURUSTU SFC SFCU CDIN5 <<•; 844 . •• . . 844 .73- .0007 
... 589 . T40 . .945 .753 . 0009 
90. 327 . 507. 1 .281 ,826 . 0010 
.000 0. 100 . 2622 3 . 26258. .293 .293 .0000 73 . 50. 26-1 . 5 .981 L . 126 .0012 
9B. 24697 . 21697. .237 .297 . 0000 
c 22202. 22202. 2 7 .287 ,0000 
a A 19510. 19510. .282 .282 .0000 .850 35000. 190 , 5163. .556 .549 .0003 
16365 - .287 .287 . OOOO 98. 4466 . 4527 . . IJA .558 . DOD3 
10 . USAC. I U86. .335 . 335 . OOOO 96. 3334. 3898, . 5L2 . 5II2 0004 
SE. 5637. 5637 , .569 .969 . OOOO 94 . •• 199, 3269 . .540 .567 .0004 
SE. 4906. 4906 . . 557 .OOOO 92 . 2545 . 2623 , , 622 .6U4 .0004 
84 . <T. • 4147 . .S38 . 528 . OOOO 90. 1847. 1 •• i '1 . .724 . 691 .0005 
8":. -5 i .0 . 3410. .507 .507 .OOOO 88. 1356 . 1458. . 822 ,764 . 0006 
. 2 595 . 2595. .505 .505 .0000 86 . 1221. .832 .749 .0007 
71. 1409 . 1609 . .583 . 1S'3 . OOOO 84 . 841. 987 . .374 ,7 45 . 0008 
82 . 5B2 . 754 . .986 .1' 3 ,0009 
80 . 31*. SIB. 1 .372 .835 , AOLI 
.750 35000. 100. 4902 . 492C • . ii 2 . 510 .OOOI 78 . 35 . 272, B .710 L .110 ,0013 
98 . 4303 . 4319 . . ::10 508 . 0001 
96 . 370.6 . 3724 . . 5 1 4 ! . 00 01 
94 . ! L03 . 3123 . .529 • 525 .OOC 1 SEA-LEVE", STATIC THRUST « 2 6 228. (MAX) 
92 . 2475. 2498 . .146 .541 .0002 SEA- LEVEL SFC = . 2 9 J 
90. 1794 . 132-1 . .659 .649 .0002 
88 . 1 31 E . 1355. .748 .727 .0003 
86 . 1086. 1136. . 744 .712 0003 
84 . 854 . 919 . ,761 . 707 .0005 OUTP.IT FOR MC.-.ULE 41 ? 
82 . 61*. 701 . . 821 .724 .0006 A + * * * * * ** *•* * . • 
EO. 375 . 47 9 . 1 .018 .797 .0007 TRAJECTORY OUTPUT 
78. 114 . 242 2 .375 1 .115 .0009 
MISSION 1 (PAYLOAD = 9 6<"'0_-. LB) 
.775 35000. .' ;;0. 1951. 4372 . . 532 . 520 .0031 PHASE M H CL AJ.I'HA 'TFIL 1 I11E 
3 8 . 4 42 . 436.1, .52D . 51 3 .OOOI SFC 11) 1 HRUST(I) CD GAKHA W WA 
9O - 3738 . 3761 , 
. 'JJS 
.522 . 0001 HRUST (LI; COINST L/D THR/THA PR 
94 . 31.-. 8. 1154. 540 .536 .OOOI 
S2 . 2494 . 2524. . 574 . 571 .0002 WARM 'Vf 0. 6490 ,1 30 .00 
90. 1E03 164*. . 673 . 662 . 0002 . 50 25711. 
11.. 1330. 117S. .763 .73 6 . OOOI 
B6. 1092 . LLSI. .743 . 721 . UUU4 TAKEOJF .25 0 . 2 .1669 12 . 00 5 7 • 5 .50 
NOV IS 96 15:07:47 
2ND SEG 
CLIMB 
CYCLE 
ACCEL 
CYCLE 
CLIMLI 
VycU 
CRUISE 
CYCLE 
C-
CYCLE-
36 17 6780 .*173 1" 13 73IAOE.S 895 1 85 
.36 176780 .0003 1 6: 1.00 1 00 57D7 
.25 400 . 2.IV63 00 i . : 
.36 154683. .4173 20.21 701608.5 H95 .9 89 
.36 176780. .0003 2 •; 1.00 1 .00 
.46 1QDO0, . 6259 •2 2 <;•:•; .7 3 •4 491 
.44 117490. .0348 5 00 773863.6 6 S5 212 
.44 117663. .0001 • 1 59 . . C 0 1 00 14 
.51 10000, . S053 5 46 281 . J 32 54} 
. 46 115Z16. .0274 00 778582.I 715 94 165 
.46 115*21. .0001 18 4? J. .00 1 OC 2 
. 80 33UU0, . 5401 5 21 9446.7 15 30 788 
. 57 52 1 14. .0265 86 769135.4 366 45 247 
.57 52724. .0001 18 94 1.00 1 00 103 
. 8J 3*2« . .4768 4 45 95476.6 258 13 823 
. S 5 37290. .C263 00 673659.0 5 244 
.50 37733. .0003 IB 14 . SO 1.00 JILL 
• 5 42513. .4S<3 4 55 176193.0 SO: 94 AS 3 
27 . . ). -0266 00 495465.9 226 7 V 177 
. -- 1 27659. . 00D3 18 18 . 6U 1 00 4899 
747-ACSYNT-OUT 
LUND INS THRUST TC WEIGHT RATIO. • .398 
TWKTWFE WEIGHT • 7BBM1. LBA 
LANDING WEIGHT = 472323, LBS 
DESCENT .49 0. .3D75 5.17 1HD.5 15.67 547. 
.73 15581 .0276 5.15 49375,5.5 5 77.31 356. 
CYCLA .73 15486. .0001 1B.4S .10 1.00 101. 
V• LEGS 
CLIMB .7B 35000. .3994 3 36 6676 . 6 12 04 758 
. 5? 39673. . 0217 1 52 437078.9 305 50 212 
CYCLE . 52 39843 . .0001 la 39 • 12 1 00 7J 
CHUISE .85 35000. . 3273 3 02 6017.4 21 SB 827 
. 56 23490. . 0211 00 481061.5 310 253 
CYCLE .55 30018. .0004 16 I'.I .60 1 00 176 
LOITTVH . 10 1500 . . 7 4-! 8738.0 30 IJO 333 
.64 27253. . 0371 00 472323 . 1" 673 07 HI 
CYE.I - . 64 2 7 2 =• •* . . 0001 17 67 . I 7 1 00 'J3 
LANDING .23 0. 2.1642 12 00 2O0 
.16 17B543 . .8161 19 81 598326.3 892 17 SO 
.30 176678. .0003 2 65 I.00 1 00 6708 
FUEL SUMMARY 
TOTAL ?UE'. 
MISSION F*IAJ 
RESERVE FUEL 
TRAPPED FUETL 
335241. 
31*447. 
1D40 . 
TAKEOFF FUEL; 
TAJIEOTF = 
FUEL LPBIJ: 
6490. EKTETNAL = 0. 
522 . INTERNAL - 33 5241. 
FDLNTK TIME 
BLOCK HAPGE 
SLUCK FUEI 
15.431 HTS 
7230.8 N.M. 
295065.4 IN. 
TAKEOFT FIELD LMGTTI (TOTAL RUN) = 5707. FT 
LANDING FIELD LEIIFLTH (TOTAL RUN! = 670B. TT 
LANDING FIELD LENGTH (GROUND RUN) = 3I67. ET 
WEIGHT [OR LONGING CSLCULATIAN = 598326. LBS 
POCOL I .250 GS 
JNOV 18 % 
3 5:07:47 747-ACSYNT-OUT 
IT-AJAC'X'KR OUTPUT 
MISSION 2 { I'AYLOAD -. 3 6000. LB) 
PHASE M H CL ALPHA WFUEL 3 I HE VEL 
SI-EL; ; THRUSTFI) CD B VA Q SFC(U) THUU5T(U) CDINST L/D THR/THA PR 
U~ i} . 6490.1 30 .00 
.50 2S711. 
TAKEOFF ..a 0 . 2 .1617 12 .00 522 . 5 . 50 245 . 
.35 180420. B2.50 14 .67 625719.6 889 .02 72 . 180420. 0003 2 . 65 1 .00 1 .00 4161 . 
2ND SEG , 22 400 . 1617 12 . 00 245 . 
. 35 157867. . 8150 15 . 83 623719.6 72 . 
. 3 5 180420. 0003 2 .65 1.00 1 .00 
C: 1MB .46 10000. 4995 5 . 47 2141.4 2 .21 JS1 . 
.44 117490. 0272 7 . 74 6S357B.1 695 . B B 212 . CYCLE .44 117663. O0Q1 13 .37 1. 00 1 . OO 
: 1 
ACCEL . 51 10000. 4047 4 .33 201 .3 .23 549 . 
. 46 115216. 0226 .00 623376.8 716 .94 2 65 . CYCLE .46 115121. O0QL 17 .94 1 . 00 1 .00 1 . 
.30 33UC;. 43 36 i 1 5 •FL2I.& 9 . B 7BH. 
.57 52544 . 0231 1 .79 617551.9 366 .45 217 . 
CYCLE .57 52724. 0001 18 .74 1 .00 1 .00 62. 
CRUISE .85 35S4SI . 3823 3 . 54 66594.6 210 .94 •RL. 
55 3 1 930. 0221 . OO 550957.i 3 03 .94 2 0" . CYCLE . 55 32412. 0001 17 . 31 . 67 1 . 00 1727 . 
CRUISE .85 33151. 3 9 J7 3 . 62 64771 ,9 .06 823 . 
.55 28F . D224 .00 486185. 26» .45 215 . CYCLE .5.5 •JB-43 . 0003 17 .42 . 67 1 R. F 1910 . 
DESCENT .49 0 . 2992 5 is 3 • I 4 5 . O 11 28 343 . 
.71 ±5 07". 0276 5 3 0 481540.4 590 BS 350. CYCLE -72 161H3 . O001 18 14 . 11 1 CO 6
 9 . 
J.ESERVE LEGS 
CLIMB .78 35000. 3920 3 78 S4RQ.0 11 66 758. 
. 52 39673. 0214 59 476060.5 305 50 212 . CY C 1 E . 52 
3',' o 4 3 . 0DO1 IS 31 .82 1„ 00 71 . 
CRIJ1SK .85 35000. 3216 2 90 6047.0 21 88 B27 . 
.57 25;Ml. 0199 00 472013 . 5 309 97 253 . CYC I F> .56 29717 . 0004 16 17 . 60 1 00 179 . 
LOITER .30 1 500 . 643 0 7 33 8518.4 TO r. 333 . 
. 64 26621. 0362 HI- 463495.0 671 125 . CYCLE . 64 2*667. 0001 
•:• . 16 99 . 
IJLFIURNG .22 0 . 2 1616 12 ,0 24 5 . 
.35 I 80446. 8150 17 3 ] 531198.9 '•8 71. .35 IFTD5T3 . NNO3 2 65 1.00 1 00 5937. 
RESEI'JE Fuel = 299J7. 
TNJIPED Fuel * 101D. 
BLOCK TIME SLOCK RANGE 
BLOCK FUN] 
TAJCAOE 6 
8.375 HRS = 1196.7 RI.M. 
= 14B1J1 fi lb. 
5937. 292 . . 
'LAKEOFF FIELD LENGTH (TOTAL RUN) LANDING FIELD LENGTH I TOTAL RUN) 
LANDING PIULD LENGTH (GROUND RUJIL HEIGHT FOR LAJIILLNG CAL Z-^LATI CN - 531199. 
LANDING THRUST TO WEIGHT RATIO - .I40 TAKESFF WEIGHT = 632732. 
LANDING WEIGHT - 4634J5. 
i L IT 
FT 
LBS LBS 
FUEL -•sU^VR.ARY 
TOTAL PU«l • :7JIFC8. Takeoff FUAL: LOT 
MISSION FUEL = 169237. WARNIUP = 6490. EXT 
747-ACSYNT-OUT 
OUTPUT FOR MODULE # 6 
******** 
QMAX: 
DESIGN LOAD FACTOR: 
ULTIMATE LOAD FACTOR: 
STRUCTURE AND MATERIAL; 
WING EQUATION; 
BODY EQUATION: 
COMPONENT 
WEIGHT STATEMENT - TRANSPORT 
***** 747-40O WEIGHTS »**»* 
400, 
2 .50 
3 .75 
ALUMINUM SKIN, STRINGER 
AIR FORCE EQUATION 
AIR FORCE EQUATION 
POUNDS KILOGRAMS PERCENT SLOPE TECH FIXED 
AIRFRAME STRUCTURE 226308. 102654. 28 69 NO 
WING 104204. 47267. 13 21 1 15 1 00 NA 
FUSELAGE 70405. 31936, B 93 1 36 1 00 NO 
HORIZONTAL TAIL ( LOW) 7989 . 3624. 1 01 1 00 1 00 NO 
VERTICAL TAIL 4140 . 1878. 52 1 08 1 00 MO 
NACELLES 4778. 2167, 61 80 1 00 NO 
LANDING GEAR 34793. 15782. 4 41 1 00 1 00 NO 
PROPULSION 40262. 18263. 5 10 NO 
ENGINES ( 8) 33215. 15066. 4 21 1 00 1 00 NO 
FUEL SYSTEM 3796 . 1722 . 48 1 36 1 00 NO 
THRUST REVERSER 3251 . 1475 . 41 1 25 NO 
FIXED EQUIPMENT 65504. 29713. 8 30 1 00 NO 
KYD & PNEUMATIC 4998. 2267. 63 06 NO 
ELECTRICAL 4859. 2204 . 62 1 06 NO 
AVIONICS 2238. 1015. 28 1 06 NO 
INSTRUMENTATION 1339 . 608. 17 1 06 NC 
DE-ICE & AIR COND 5341. 2423 . 68 1 06 NO 
AUX POWER SYSTEM 762 . 345 . 10 1 06 NO 
FURNISH & EQPT (11408 . 18782. 5 25 1 06 NO 
SEATS AND LAVATORIES 21585. 9791 . 2 74 1 06 NO 
GALLEY 6773 . 3072 . 86 1 06 NO 
MISC COCKPIT 247 . 112 . 03 1 06 NO 
CABIN FINISHING 9398 . 4263. 1 19 1 06 NO 
CABIN EMERGENCY EQUIP 2349. 1066. 30 1 06 NC 
CARGO HANDLING 1055. 479 . 13 1 06 NC 
FLIGHT CONTROLS 4560 . 2069 . 58 1 06 NO 
EMPTY WEIGHT 332074. 150629. 42 10 
OPERATING ITEMS 0. 0. oo NO 
FLIGHT CREW ( 2) 340. 154 . 04 NO 
CREW BAGGAGE AND PROVISIONS 475 . 215. 06 NO 
FLIGHT ATTENDENTS ( 131 1690. 767 . 21 NO 
UNUSABLE FUEL AND OIL 1802 . 817. 23 NO 
PASSENGER SERVICE 20600. 9344 . TO 61 NO 
CARGO CONTAINERS 1649. 748. 21 NO 
OPERATING WEIGHT EMPTY 358630. 162675. 45 46 
FUEL 178129. 80799. 22 58 
PAYLOAD 96003. 43547. 12 17 NO 
PASSENGERS (412) 69216 . 31396. 8 77 NO 
BAGGAGE 16480, 7475, 2 09 NO 
CARGO 10307. 4675. 1 31 RES 
CALCULATED WEIGHT 788834. 357B15. B0 21 NO 
ESTIMATED WEIGHT 
PERCENT ERROR 
788821. 357809. 
.00 
CALCULATED WEIGHT DOES NOT EQUAL 100% BECAUSE A GROUP WEIGHT IS BEING FIXED. 
OY 18% 
15:07:47 747-ACSYNT-OUT 
OUTPUT FOR MODULE J J. 
1 K./MMARY AC<:'-'::'.' OUTPUT 
FN'ULISH UNITS -
1989 BOP. 1 .TO 747-400 "RAMSPORT 
DISTANC1; IN FEET 
WEIGHTS IN ! RS. 
GENERAL FUSELAGE 
'•'ORCES IN LBS . 
PRESSURES IN LBS/FT*-
NASA, AMES STEF CENTER 
HTAIL VTAIL 
WG 788B3 4. LENGTH 225 ,2 AREA 5B14 O 1470.0 3 3 0.0 
W/S 135.7 DIAMETER 20 .2 WETTED AREA 11614 F 2069.8 1072.S 
T/W .27 VOLUME 56207 .2 SPAN 211 .4 71.1 32 .0 
N (Z) ULT 3 . B WTTTEP AREA 12180 .9 L.E, SWEEP 40 .7 46 . 0 47 .5 
CREW 2. FINENESS RATIO 11 .1 C/4 SWEEP 37 .5 41.0 41 .0 
PASKNGERS412 . ASPECT RATIO 7 . 69 3.44 1 .23 
TAPER RATIO 1 I; .27 . 29 
E11G :NE WEIGHTS T/C ROOT I? .11 .11 
T/C TIP U- .09 . OS 
NUMBER 1. W WG ROOT C90RE 46 .8 32 . 6 40.3 
LENGTH 7,4 STRUCT. 22 6308. 28 .7 TIP CH0RC 8 .2 8. 1 11 .7 
1 IL AM . 5.1 PROPLIL. 402 62. 5 .1 M.A. CHORD 32 ,0 22 . J 29.6 
WEIGHT 34S8.9 i ••:. KO. •). 8 .3 LOC. OF L.E. 89 .6 19 3.7 IE4 .9 
TSLS 26228. FUEL 179168. 22 7 
SFCSLS .29 PAYLOAD 96003. 12 2 
TFRSSION SUMMARY 
PRASE MACH 
VAKEOFF .00 
CLIMB . 16 
ACCEL . 5I 
CLIMB . 80 
CRUISE . 35 
CRUISE . 85 
DESCENT .49 
CLIMB .78 
CRUISE .85 
] VJ.1 THR . 3 0 
UV-KJ :.'JG 
ALT FUEL 
0 . 7013 
10000. 2141 
10000. 201 
3300U. 5825 
35*48. 66595 
38454. 64772 
0 , 164 5 
35000. 6480 
35000. 6047 
1500 . 8518 
TIME DIST 
~ _ R • -
30 5 4 ( 8 
M 2 9 9 
2 1 2 
9 3 61 6 
210 9 1727 3 
235 1 1910 2 
14 3 88 1 
11 1 71 3 
21 S 178 7 
30 0 98 7 
5987 3 
L/D THRUST 
-- =— =- " = 
1 8 37 117489 .9 
17 :'4 1 ! 5 2 1 0 
18 74 52 543 . 6 
17 31 31930 . 5 
17 42 28012 . 5 
i 44 16078 .0 
ii 31 39672 . 9 
IF 17 2 9 187 . 1 
17 75 26621 .1 
SFC Q 
.442 212.0 
.4B"0 265.0 
.57 0 54.7.2 
.1-54 248.5 
.554 214.9 
.729 J 4 3 . 3 
.524 2I2.C 
S65 252.5 
.640 12», 3 
BLOCK TIME = 8.375 HR (WITHOUT AIR AND GROUND MAMJEVER ALLOWANCES) 
BLOCK RANGE = 3798.7 NM 
Appendix C Page 56 
Appendix C. B747-400 FLOPS Input & Output File 
15:07:48 
67*7-400 (PW4056J REV <,.'.! 
SOPTIQN 
I0PT-.1, 
IANAL*3, 
TN5NG- I , 
5. MB 
SWTTN 
VRIMO: ) . ':•, 
SE>AN=2U7.6667, 
DIH 7.5, 
WFJIFKP , 244 , 
NETAW=5, 
BTW- -413, ,66, .888, 1.0. 
CUL= 54.33, JFI-JB. 20.'J6, 14.71, 13.33, 
T0C= .134, .030, .07S6, .08, .08, 
SWL^,: I. .31. ,3 4.,34., 
ETAE-.IS,.67. 
SHT-1470-. 
SWPRLT=J7 . 9, 
I' = 3.6. 
TR4T=. 3 V 
TCJW=.05, 
HHT=0. , 
SVT=83,0 . , 
SWPV: -45. , 
ARVT=1.25, 
L-RVR = .3I, 
TCV;'^.08, 
NFJK*2, 
SFIN=56.4, 
ARFTN^O .84, 
TRFIN=C.35, 
SWPF.IN-55 . , 
TCFIN=.03, 
XL-225.1667, 
WF=21.33, 
DF=2 5.75, 
XLP-187, 
XHLG=141.8, 
XMLG-LLL.7 , 
NT3N=4, 
TKRSO=56570., 
WENG=3800.0, 
XNAC=17.33, 
DKAC=11.67, 
NTANK=8, 
FULWKLK=2S0227 . , 
IFUFU»1, 
TWF"^34 , 
NPT=37 8, 
NFLCR-2, 
WSEVN . , 
WTHSU5390. , 
WFURK-41050• , 
WAC= 1 . , 
WAI-I., 
SCONFIM 
I- :•-IR,=7300 . , 
HTVC=1. , 
VTVC-1 . , 
OFO=1, 
QFT^O, 
GW'BIOOOO.. 
SW=5651., 
B747-FLOPS-IN 
TR=.245, 
S-rf£EF=37 .5, 
T \=,08, 
VCMN-0.85, 
CH=40000., 
SEND 
SAERIN 
MYAERQ=1 , 
WRATI0=O.4, 
ITPAEF.- 2 , 
IBD=1, 
>HHD 
SENGDIK 
IGEHEN-1, 
NCHUG^I, 
EMALH^. .85, .6, 0., 
AJ T (1,31 - 4000 . , 0 . , 
ALT(1,2> = 20000., 15000., 
ALTFL,1) = 39000.. 35000., 
SEND 
SEWGINE 
IENG=0, 
ITHP.OT=0, 
FLTFIL--1 PW4056 ,PS ' . 
IWTPKT=3, 
XWTPLT=0, 
IF1LE='FW4000.CONFIG', 
TPILS='PW400C MAP', 
IL?NIWT=L, 
NGINWT=-! , 
NITKAX=7 5, 
HPEXT=.0, 
COSTL3L=0, 
OFI[,fc>'OUTPUT', 
YEAR-19^5, . 
DESFN^I 5750. , 
4.0, 
OPRDES=27.7, 
HPCPR=11,5, 
FPB.-ES= I . 560, 
TETDE£=2 572., 
WCOOL=2 310., 
TTRDR,PS = L , 03, 
DTCE=15., 
ALC-1O0OJ. , 
XMDSFC- . G5 , 
XADES = 3J000 . , 
XKMAX-J.9, 
AMAX=40GQD , 0 , 
AINC-5000., 
XTF7NR=0.1, 
QKAX=800.0, 
U7IPI=1150 . , 
RH2T1=.35, 
TP.DAN2 = 3 .5, 
JILR=L .1, 
XHLOD=.611, 
XBLD2-1 . 58, 
RADJ.-= . 17 3 , 
IMAOL, 
Nov J8 96 
15:07:48 
NVAB*4, 
SHI3SIM 
B747-FLOPS-IN 
I FLAG >-2 , 
MSUMPT=0, 
IRW-1, 
IATA-^0 , 
FCD0=L.0, 
FCDI^L,JR 
TAXOTM=10.0, 
TAKOTM=2.0, 
NCLIMB=I, 
CLMMIN=0.3, 
C1,AMIN=0 . 0, 
FWF = 1.0, 
IPPCL-1, 
NCRUST=3 , 
IOC- 0, 3 , 
CRALT= 40000.. 30000., 
CRKACH- '1 ?1, 0. 85 
CRMMIN= 0.5. 
S. i, CRDCD= 0.0, 0.0, FLRCR- 1.0, 1,0, CRCLMX= 0.8, 0.8, 
KCIN-300 . , 
IVS=1. 
DEAMIN^O.0, 
DEMMIN-0.3, 
DEDCD-0.003B, 
IRS=1, 
RESTRP=.05, 
TIMMAP=2.0, 
ALTRAN=30Q.0, 
NCLRES=1, 
NCRRES=2, 
HOLDTM=30 .0, 
N(.:RJIOL=:T, 
1JI0P0S=1, 
ICRON '), 
EREALT-1500,, 
4, 
1500., 
0.7, 
0 .25, 
0 .0, 
1 .0. 
1.0, 
$ENE 
START C 
CLIMB 1 
CRUISE 1 
DESCENT 
END 
E N 
0 .30 
0 .00 
0.80 
0.01930 0.01810 
0.05520 
0,01750 0.01630 
0 . 0542V: 
0.01720 0-01600 
0,06100 
0.01730 O.L'1&40 
0.06470 
0.01800 0.01650 
0.07260 
0,01840 0.0168C 
0.17620 
0.01940 O.QLHLQ 
0.08960 
0.5C 
O. IC 
0.70 
0 . 13 
0.O1800 
0 .01 R,::I-
0.01590 
0 .01630 
0.O1640 
0.01670 
o, L'LIOO 
0.80 
0, 20 
0.01840 0 
0.056*0 0 
0.01630 0 
0.01670 0 
0 . 01 6 S 0 0 
0.01720 0 
0.01840 0 
0,84 0.86 0.88 0.90 
0.30 0.40 0.44 0.50 0.60 
,02020 0.02300 0.02480 0.0278O O.O3430 
.01840 0 0^120 0.02320 Q.0JJG60 0.03330 
.01810 0.02090 0.02260 0,02550 0.03330 
1.11850 0.02 L20 O.02310 0.02620 0.03440 
.01870 O.02140 0.02320 0.O2680 O.O3450 
.01900 0.02180 0.0235O 0.02730 0.03690 
.02020 0.02300 O.M^U 5.02950 0.04160 
0.70 
0,04320 
0.0420C 
0.04520 
0.04370 
0.O5180 
0.05570 
0.06400 
0,02100 
0.10830 
0.01970 Q.OLSFIO 0.0VO0O 0.02210 O.025RO 0.O2S9Q 0.031QQ 0,04950 0,07 
40000.0 45000.0 
10 8 
0.0 5000.C IOOOO.O 15000.0 20000.0 25000,G 30000.0 35000.0 
0.30 0.50 0.70 0.8O 0.84 0.36 0 .88 0 . 90 
-0 0017 -0 0016 -0 0014 -0 0014 -0 0014 -0 0014 -0 0013 -0 0013 
-0 0015 -0 0013 -0 0012 -0 0012 -0 0012 -0 0012 -0 0012 -0 0011 
-0 0012 -0 0011 -0 OOIO -0 0010 -0 OOIO -0 0010 -0 0009 -0 0009 
-0 OOIO -0 0008 -0 0008 -0 0008 -0 0008 -0 0007 -0 0OO7 -0 0007 
-0 0007 -0 0006 -0 0005 -0 0005 -0 0005 -0 0005 -0 0005 -0 0005 
-0 0003 -0 0003 -0 0003 -0 0003 -0 0003 -0 0003 -0 0003 -0 0003 
0 OOOO 0 OOOO 0 OOOO 0 OOOO 0 OOOO 0 OOOO 0 OOOO 0 OOUO 
0 0004 0 0003 0 0003 0 0003 0 0003 0 0003 0 0003 0 0003 
0 O009 0 0008 0 0007 0 0007 0 0007 0 0007 0 0007 0 0007 
0 0014 0 0013 0 0012 0 0011 0 0011 0 0011 0 0011 0 OOII 
B747-FLOPS-OUT 
1 ENUINE LOCATIONS ETAE . JBO0 
•TITLE, BEGIN INPUT DATA ECHO LOAD DISTRIBUTION CONTROL PDIST 
2.0C B747-4DD (FW405*) REV 2.0 HORIZONTAL TAIL DATA 
AREA SHT 1470.00 SQ FT 
1/4 CHORD SWEEP ANGLE SWtHT J7 ,Su DEG 
ASPECT RATIO AKHT 3 . GO 
* NAMELIST 90PTIGN 3A:-L.-. RATIO TRHT .250D PROGRAM CDHTRCL, EXECUTION, ANALYSIS AND PLOT OPTION DATA T/C TCKI .0800 LOCATION ON VERTICAL TAIL HHT , 0000 
DESCaiPTION NAME VALUE DIMENSIONS 
VERTICAL T\IL DATA 
TYPE OF PKOHT.f.M IOPT 1 NUMBER OF VERTICAL TAILS NVSRT 1 
ANALYSIS OPTION I ANAL 3 AflSA SVT 830 SQ FT 
MAIM ENGINE DECK SWITCH 1:. • NG 1 1/4 CHORD SWEEP ANGLE SWPVT 45 . JO DEG 
Le.iAILED TAJT-Jur-T SWITCH 
ITAKOF 0 ASPECT RATIO AEVT 1.2500 
DETAIIiED LAMIJING SWITCH I LAND •': TAPER RATIO T'RVT . 3400 
COST CALCULATION irosT 0 T/C TCVT . 0800 
TRAUSPOKT/FIGHTER SWITCH TFITE 0 
TAKEOFF PROFILE TOK NOISE NOPRO •: WING K'-N DATA 
PftOFlLE OUTPUT FILE SWITCH NPF1LE '.: ''A SFIN 56,40 SQ FT 
NOISE CALCULATION;; 3WITCH NOISE 0 ASPECT RATIO ARFIN . 8400 
KASTE3 PRINT CONTROL 
MFKINT 1 TAPER RAT 10 TRFIN .3 500 
XPLOPS DATA PLOT SWITCH 
T.XFL n T/C TCF J .0800 
AERO POLAR PLOT SWITCH IPOLP 17 ]/4 CHORD SWEEP ANGLE SWPFIN 55.00 DEG 
THHU.^T DATA PLOT SWITCH I PLTTH !.! NUMBER OF FINS NF N 2 
HISTORV DATA PLOT SWITCH IPLTHS 0 
EXCESS POMES PLOT SWITCH i PiiTfS 0 FUSELAGE DATA 
NUT5BER OF FUSELAGES NFUSE 1 
TOTAL, LKNtffH XL 225.17 FT MAXIMUM WIDTH WF 21.33 F'i t NAMHLIST ?WTIM MAX T MUM DEE'Til DF 
2S.75 
FT. 
GEOMETRIC, WEIGHT, BALANCE AND INERTIA DATA CARGO AIRCRAFT FACTOR CARGF .GOOD 
PASSENGER COMPART LfcMGTH XLP 187.00 FT 
DESCRIPTION NAME VALUE DIMENSIONS 
LANPTNiS G:- • • DATA 
MAX OPER KAC'ji NUMBER VMMO . 8500 LENGTIT CP MAIN GEAT> XMLG 141.60 IN 
UiTIMATE LOAD FACTOR UL.- 3.7500 LENGTH OF NOSE GEAR XNLG 1 .70 IN 
REF WEIGHT MUMfiER N'.'.'REF 39 DESIGN Lk'..': • '• WEIGHT WLDG 3480DO.0 LBF 
CG REFERENCE LENGTH CGREFL 2702.0 IN SET WLDG TO END OF DESCENT KT.DWT 0 
X KOR START OF CGREFJ. CGREFX .0 IN CABRtE* BASED AIRCRAFT CT.RBAS . 00 
SWITCH TO COMPUTE WEif-H'fJi WYWT5 0 
DtilcU GROSS WT, 1 RATIO) DGW 
i. ooo PROPULSION SYSTEM DATA HYDRAULIC SYSTEM PRESSURE HYDPR 3000. NUMBER OF ENUINE9 ON WING NEW 4 NUMBER OF ENGIKES ON FUSE 0 
WING DATA BASELINE ENGINE THRUST TIIR-JO 56570.0 I.SF 
DIH3DRALIPOSITIVE) DIH 
7.000 DEG 
BASELINE ENGINE WEIGHT WENG .•800.0 i.SF 
GLOVE AND BAT AREA GLOV .00 SQ PT WEIGHT SCALING PARAMETER EEXP 1.15000 
SPAN SPAN 207.67 FT BASK1.IWE INLET WEIGHT WINL .0 LBF 
CONTROL SURFACE AREA RATIO FLAPR . 2440 INLET WT SCAL:NG -KXPOWENT EIN1 1.00000 
FRACTION OF COMPOSITES FCOMP .0000 BASELINE NOZZLE WEIGHT WNOZ .0 LBF 
A5ROEI.ASTIC TAILORING FACT FAERT .0000 MOAITLE WT SCALING EX FOMENT SNOZ 1.00000 
STRUT BRACING FACTOR FSTRT .oooo BASEL!ME NACELLE LENGTH XKAC 17 . 33 FT 
VARIABLE SWEEP FACTOR VAPSWP .OOOO BASELINE NA-ELLK DTAMETKH PHAC 11 . 67 FT FUEL
 CAPACITY OF WING 
FULWMX 2502/7.0 LBM 
DETAILED WING "EFT "M DATA FOR 5 ST! iTTONS IFOEL. CAPACITY FACTOR •..MAX 24.151: 
 CAPACITY OF FUSELAGE FUUHX .0 LBM 
STATION DATA 7 2 3 4 5 AP>J"JiT FUSE FUEL CAPACITY IFUFU 1 
0 V/SEMISPAN ETAW .4130 . r.roo .S8S0 1 L'UOL' AUXIL TANK KOBE, CAPACITY FULAUX . 0 LBM 
0 CHORD/SEMISPH.' CUB 54.3300 28.98C0 20.5£00 14. • : 13 
3 7 00 
NUMBER OF FUEL TANKS NTANK 8 
THTCKNEv.* • h'-'r.O TOC . 1^,40 .0900 , 07K6 . OBOO O&oo AL4JED H1SC PROP SYSTEM WT WPKISC . 000 LBF 
0 LOAD PATH SWEEP SWL 21 .00 34.00 34.00 34 .00 . 00 
0 fiKPSflENCE ASPECT RATIO AKREF 7 . 6.1 CKKW AWP PAYLOAD DATA 
REFERENCE THICKNESS/CrtTJRp TCKF.r . IJSOOO FIRST CLASS FASSl-^ERS NPF 34 
FRACTION OF LOAD ON DEFINED TOURIST PASSENGERS MPT J !i 
Iv'lUG (OH PEF WING AREA) 
PCTL 1.0000 STEWARDESSES VSTU -1 
HO. OF INTEGRATION STEPS N . I J0 GALLEY CREW N;;ALC -1 
I-70C 
Nov 18 96 
15:07:49 B747-FLOPS-OUT 
FLIGHT CREW NFLCR 2 AUXILIARY GEAR CGAI .0 IN 
WEIGHT PER PASSENGER WPPASS 165 .0 LBF AUXILIARY TANKS CGAUT ,0 IN 
BAGGAGE PER PASSENGER SPP 44. 0 LBF AMMO AND NONFIXED GUNS CGAMMO .0 IN 
CARGO IN WING CARGOW .0 LBF MISCELLANEOUS USEFUL LOAD CGMIS .0 IN 
CARGO IN FUSELAGE CARGOF .0 LBF 
OVERRIDE PARAMETERS FOR WEIGHTS It NAMELIST SCONFIN 
WING - TOTAL FRWI 1 .OOOC GEOMETRIC RATIOS, OBJECTIVE FUNCTION FACTORS, AND DESIGN VARIABLES 
WING WEIGHT FIRST TERM FRWI1 1 ,0000 
WING WEIGHT SECOND TERM FRWI 2 1 .0000 DESCRIPTION NAME VALUE DIMENSIONS 
WING WEIGHT THIRD TERM FRWI3 1 .0000 
HORIZONTAL TAIL FRHT 1 ,0000 DESIGN RANGE DESRNG 7300.0 N MI 
VERTICAL TAIL FRVT 1 . OOOO WING LOADING REQUIRED WSR .00 
WING VERTICAL FIN FRFIN I .0000 THRUST/WEIGHT REQUIRED TWR .00000 
CANARD FRCAN 1 .0000 GLOVE/WING AREA REQUIRED PGLOV .00000 
FUSELAGE FRFU 1 .0000 HORIZ TAIL VOLUME COEF HTVC 2.152473 
NOSE LANDING GEAR FRLGN 1 .0000 VERT TAIL VOLUME COEF VTVC .159254 
MAIN LANDING GEAR FRLGM 1 ,0000 COST CALCULATION SWITCH ICOST 0 
NACELLES - TOTAL OR FRNA 1 .0000 
AIR INDUCTION SYSTEM FUNCTION TO BE OPTIMIZED - 9BJ = 1. OOOO*(RAMP WEIGHT) + .0000*FUEL 4 .0000" 
THRUST REVERSERS - TOTAL WTHR 5390 ,0000 + ACHML/D) 4 
MISC PROPULSION SYSTEMS WPMSC 1 .0000 0000*RANGE 4 .0000*COST 4 .0000* (NOX EMI 
FUEL SYSTEM WFSYS 1 .0000 4 SIONS) 
SURFACE CONTROLS FRSC 1 .0000 
AUXILIARY POWER UNIT WAPU 1 .OOOC 
INSTRUMENT GROUP WIN 1 .OOOC DESIGN VARIABLE DATA 
HYDRAULICS GROUP WHYD 1 .0000 
ELECTRICAL GROUP WELEC 1 .OOOO VARIABLE NAME VALUE ACTIVITY LOWER BOUND UPPER BOUND 
AVIONICS GROUP WAVONC 1 .OOOO + SCALE FACTOR 
ARMAMENT GROUP WARM .0000 
FURNISHINGS GROUP WFURN 41050 .0000 RAMP WEIGHT, LBF GW 870000.0 0. .0 .0 
AIR CONDITIONING GROUP MAC 1 ,0000 + .00000 
ANTI-ICING GROUP OR WAI 1 .OOOO WING ASPECT RATIO AH 7.6315 0. .0000 .0000 
AUXILIARY GEAR + .00000 
UNUSABLE FUEL WUF 1 .0000 THRUST PER ENGINE, LBF THRUST 56570.0 O, .OOO .000 
ENGINE OIL WOIL 1 .0000 4 ,00000 
PASSENGER SERVICE OR AMMO WSRV 1 .OOOO REF WING AREA, SQ FT SW 5651 .0 0, .0 .0 
AND NONFIXED WEAPONS 4 .00000 
CARGO AND BAGGAGE CONTAIN, WCON 1 .0000 WING TAPER RATIO TR ,24500 0. .00000 .OOOOO 
OR MISCELL. USEFUL LOAD 4 .00000 
AUXILIARY FUEL TANKS WAUXT 1 .0000 WING 1/4 CHORD SWEEP, DEG SWEEP 37.50 0. .00 . 00 
FLIGHT CREW AND BAGGAGE WFLCRB 1 .0000 4 .00000 
CABIN CREW AND BAGGAGE WSTUAB 1 .0000 WING T/C TCA .08000 0. .00000 .OOOOO 
4 .00000 
HORIZONTAL CENTER OF GRAVITY DATA CRUISE MACH NUMBER VCMN .85000 0. .00000 .OOOOC 
KING CGW .0 IN + .00000 
HORIZONTAL TAIL CGHT .0 IN MAX CRUISE ALTITUDE, FT CH 4O000.0 0. .0 . 0 
VERTICAL TAIL CGVT .0 IN + .00000 
WING VERTICAL PINS CGFIN ,0 IN TURBINE INLET TEMP (RI ETIT .00 0. .00 .00 
CANARD CGCAN .0 IN 4 .00000 
FUSELAGE CGF .0 IN OVERALL PRESSURE RATIO EOPR .000 0. .000 ,000 
NOSE LANDING GEAR CGLGN ,0 IN 4 ,00000 
RAIN LANDING GEAR CGLGM .0 IN FAN PRESSURE RATIO EFPR .OOOC O. .OOOO .OOOO 
TWO FORWARD ENGINES CGEF . 0 IN + ,00000 
ONE OR TWO AFT ENGINES CGEA , 0 IN BYPASS RATIO £8 PR , OOOO 0. .0000 .OOOO 
AUXILIARY POWER UNIT CGAP .0 IN 4 .00000 
AVIONICS GROUP CGAV .0 IN THROTTLE RATIO ETTR .00000 0. ,00000 .00000 
ARMAMENT GROUP CGARM .0 IN 4 .00000 
FLIGHT CREW CGCR .0 IN 
PASSENGERS CGP .0 IN 
CARGO/EXT STORES IN WING CGCW .0 IN 
CARGO/EXT STORES IN FUSE CGCF .0 IN f NAMELIST $AERIN 
FUSELAGE FUEL CGZWF .0 IN AERODYNAMIC OPTIONS AND APPROXIMATE TAKEOFF AND LANDING DATA 
WING FUEL CGFWF ,0 IN 
AIR INDUCTION SYSTEM CGN .C IN DESCRIPTION NAME VALUE DIMENSIONS 
AIR CONDITIONING CGAC .0 IN 
v 18 96 
15:07:49 
AERODYNAMIC INPUT NKTHOT) MYAERO 1 
WAVE DRAG INPUT SWITCH [WAVE 0 
WAVE DRAG FACTOR FWAVE 1 . OOOO 
LLFJLAR/^AR.-V:.: I!. 1 r IN .-KL'.P ITPAER 2 
AERO MATE IK FORKAT SWITCH 160 1 
MAX SFTMBB* AT 70 PERCENT 
SEKISPAM CAM OOOOO 
AIRCRAFT LYALJE AREA B'BASE . 0 .SQ 
WJNC TECHNOLOGY S. :• K 1 . 0 
HODIFV EDET DATA HODARO 0 
FIXED DESIGN CL FCLDES -1 .OOOO 
TURBULENTiLAM ZNAR FLOW HLLAH .0 
.'.KP.N -FK LC1FNCY FACTOR E 1 . OOOO 
OVERRIDE PARAM1'': EI<3 FOR WETTED AREAS 
WTJBO WF.TTED AREA SW- ;1 1 .OOOO 
HOR. TAIL WETTED AREA ! ... . H 1 . OOOO 
VERT. TAIL WETTED AREA 5WETV 1 . 0DO0 
FUSELAGE WETTED AREA sww 1 . OOOO 
NACELLE WETTED AFEA S'N • N 1 . OOOO 
TAKEOFF AND LANDING DATA 
RATIO OF MAX. LANTUHG WT. 
TO MAX. TAKEOFF WT. WWATTQ .4000 
MAX. LANDING VELOCITY VAPPR 150 . 0000 KTS 
KBTH. TAKEOFF FIELD LIBKCHB FLTO 12 OOO.O FT 
MAX. LAN]!TNG FIELD LENGTH FLLDG 12000.0 FT 
MAX. •-- L.'JDIUR'F CONFIG. CL" 1 2 . OOOO 
MAX. CL LANDIN3 CONFI!-. C DM 3 , OOOO 
APPHI^CH CL CLAPP . OOOO 
AIR DENSITY RATI!) DRAT 10 1 . 0D00 
L/D RATIO 2KD SEG. CLIMB EIJCIKJS . OOOO 
L/D RATIO MIESED APPROACH ELCDMA , OOOO 
THRUST PER ENGINE TAKEOFF THROFF . OOOO 
THRUST PER ENGINE 2ND 
SEG. CLL'MB THRSS . 0 LBF 
THRUST PER ENGINE MISSF.D 
APPROACH THRMA .0 LBF 
NAMELIST SLNGDIN 
ENGINE DECK CONTROL, SCALING AND USAGE DATA 
DESCRIPTION VALUE DIMENSIONS 
ENGINE DECK PRINT CONTROL NGPAT 1 
ENGINE DECK SOURCE SWITCH 1'GKNEN
SLOPT: FACTOR FOR 
EXTRAPOLATING FUKL EKTFAC 1.0000 
SUBSONIC FUEL FLOW FACTOR FPPSUTJ 1.0000 
SUFESSONIC FL':-::. FLOW FACT FFFSUP 1.0000 
FLIGHT IDLE SWITCH IDLE 1 
TUNOPE NEGATIVE THRUSTS N::NEG L 
MTU ILLE FUEL FLOW FRACT FIDMIN .0800 
MAX IDLE FUEL FLOW FSACT FIDMAX 1.0000 
SFC IIXTMPOLATION SWITCH IXTRAP 1 
PART POWER DATA SWITCH IFILL 2 
MAX. CRUISE POWER SWING HAXCR
BOOST ENGINE SWITCH BOOST .0000 
FUEL FLOW SCALING 
CONSTANT TERM DFFAC .0000 
. LOW SCALING 
LINEAR TERM FFFAC .0000 
NITROGEN OXIDES SWITCH WOX 0 
INSTALLATION DWG T'V;ITCC -NSIMG
B747-FLOPS-OUT 
MAC] I NUMBERS AND ALTITUDES POP. FCBHGFFL DECK GENERATION 
MACH ALTITUDES 
.SI 3SD00. 25D0D. 
.60 20000. 15000. 
.00 4DOD. 0. 
NAMELIST SEHGIUE 
ENLILNE CYCLE ANALYSIS INPUT DATA 
DESCRIPTION V?\L.UE DIMENSION? 
USER L^.J-LRF.]".- ENGINE 
ENGINE CYCLE DEF. FILE 
IENG 
IFILE 
COMFUNXNT MAP TABLES FILE TFILE 
PRINT LCVEL INDICATOR IPR1NT 
PRINT VIB/ANOJ'F I::ATA SPRINT 
PPINT LEVEL FOR HEIGHTS IW7PRT 
PLOT ENGINE SCHEMATIC IWTPLT 
CYCLE ANALYSIS OUTPUT PILE OFILE 
PW4000.CONFIG 
PW400Q.MAP 
1 
0 
2 
0 
OUTPUT 
FLAG TO GENERATE A DECK GENDER F 
SWITCH FOR HEIGHT CALCS NGJNWT 4 
(0=NONE, L^ENGINE, 2=1 + INL1-T, 3=2 +NACEI.LE, If 
PART POWER BATA CONTROL ITHRCT 0 
NUMDER OF A/3 POINTS NL'AB
NUMBER OF DRY POINTS NPDRY 15 
PART POWER THRUST CUTOFF X1DLE .05000 
MAX ALLOWABLE ITERATIONS NITMAX 
DE.7IGW POINT DATA 
DESIGN POINT NET THRUST DE5FN 56750.0 
OVERALL PRESIRJ.KK HATIO 0PE3ES 27.7000 
FAN PRESSURE :\ATIO FPTTUFLS 1.5600 
BY?ASS RATIO BPRTJES 4.000' 
DESIGN TURBINE INLET T.-.Ki' TETDES 2572, 0 
DESIGN THROTTLE HA'I'IO TTRDBS 1.O300 
OTHER J-IGINE CONFIGURATION DEFINITION DATA 
3+NOZZLEI 
FLAG FOR AFTERBURNER. AEURN F 
FLAG FOR DUCT B'JKNEP. C URN F 
AFTERBURNER EFFICIENCY T,.-FAB 85000 
MAX APTESBURMEN TER? .'ABKAX 3 500. 0 DEG R 
FLAG FOR VARIABLE NUZZLE VEN F 
CUSTOMER COMPRESSOR BLEED COSTHI, . OOOO LB/SEC 
TURHINE. COOLING (FROM HFC) WCOOL 2310 .OOOO FKAC'TL ON (OR T41 R) 
CUSTOMER POWER EX'-'P-ACT 1 CN HFEKT .00 . P 
FUEL HEATING VALUE FHV 18 500 0 STU/LD 
TECHNOLOGY AVAILABILITY YEAR 19R5 . . • \R 
FLAG TO DO BCATTA F J. DRAG BOAT F 
DELTA TEMPERATURE DTCE 15 .00 CEG C 
DTCE VARIES TO 3£RO AT ATC 1 OOOO. FT 
FLAG TO OO SPILLAGE CKAB STILL F 
FLAG TO DO LIP DRAG LIP F 
USED TO DEFINE MACH-ALT I T' IDE ARRAY POINTS 
MAXIM'IM MACH NUMBER XMMAX .9000 
MAXIMUM ALTITUDE AMAX 40000.0 FT 
INCREMENT IN MACH NUMBER XHINC .1000 
INCREMENT IN ALTITUDE AINC SOOO.O PT 
MINIHUH DYNAMRC PRESSURE QMIN 150.00 FSF 
XAHIMUW DYNAMIC PRESSURE: Q.IWX 800. DO PSF 
Nov 18 96 
B747-
ENGINE CYCLE OPTIMIZATION CRUISE CONDITION 
MACH NUMBER 
ALTITUDE 
XMDES 
XADES 
, 8500 
39OO0.0 
ENGINE CYCLE BEHAVIORAL CONSTRAINTS 
MAX COMPRESR DISCHARGE TMP CDTMAX 99999.0000 R 
MAX COMPRESR DISCHARGE PRS CDPMAX 99999.0000 PSI 
MAXIMUM JET VELOCITY VJMAX 99999.0000 FT/SEC 
MINIMUM SPECIFIC THRUST STMIN 1.0000 LB/LB/SEC 
MAXIMUM BYPASS/CORE AREA ARMAX 99999.0000 
DESIGN CONSIDERATIONS USED IN ESTIMATING ENGINE WEIGHT 
LPC RPM / FAN RPM GRATIO 
COMPRESSOR/FAN TIP SPEED UTIP1 
HUB TO TIP RADIUS RATIO RH2T1 
TURBINE MAXIMUM AN^2 TRBAN2 
TURBINE USABLE STRESS TR8STR 
COMPRESSOR USABLE STRESS CMPSTR 
INLET GUIDE VANES IGVW 
1.0000 
1150.0 FT/SEC 
.3500 
3.5000"10 IN"2-RPM"2 
15000. PSI {LOWER LIMIT) 
25000. PSI (IF POSSIBLE] 
0 (0=NON2, 1=YES, 2-VARIABLE) 
# NAMELIST SNACELL 
NACELLE GEOMETRY AND WEIGHT DATA 
DIMENSIONS ARE REFERRED TO THE INLET RADIUS (HEIGHT FOR 2D) 
!0=FIXED, 1 TRANSLATING, 2=COL INLET VARIABLE GEOM SWITCH I VAR 
LAPSING, 3=1+2) 
FLAG FOR NACELLE GEOMETRY INAC 
EXTERNAL PORTION OF CONE X1R 
INTERNAL PORTION TO THROAT X2R 
CONE HEIGHT AT COWL LIP R1R 
CONE HEIGHT AT THROAT R2R 
ANGLE FROM THROAT TO ENG ANGLE 
COWL LIP ANGLE CLANG 
COWL THICKNESS AT ENGINE RADD 
< 1) 
NOZZLE VARABLE GEOM SWITCH NVAR 
2) 
WEIGHTING FACTORS AND LENGTH TO DIAMETER RATIOS ARE COMPUTED IF < 0 
CENTERBODY TO THE THROAT WTCB1 -10.00000 LB/SQ.IN 
CENTERBODY THROAT TO ENG. WTCB2 
COWL TO ENGINE FACE WTINT 
NACELLE EXTERNAL SURFACE WTEXT 
NOZZLE WTNOZ 
NOZZLE LENGTH / DIAMETER XNLOD 
FAN NOZZLE LENGTH / HEIGHT XNLD2 
1 (AXISYMMETRIC) 
1.10000 
1.58000 
.35400 
.58500 
7.00 DEG. 
.00 DEG. 
.173 IN. (% COMPRESSOR TIP RADIUS IF 
4 (0=FIXED, l=THROAT, 2=EXIT, 3=1+ 
-10.00000 LB/SQ.IN 
-10.00000 LB/SQ.IN 
-10.00000 LB/SQ.IN 
-10.00000 LB/SQ.IN 
.611 
1 . 580 
# DESIGN INPUT SUMMARY 
DESIGN BYPASS RATIO FOR SPLITTER COMPONENT NUMBER 3 SET BY BPRDES IS 4.OO 
CUSTOMER HP EXTRACTION FOR LOAD COMPONENT NUMBER 14 SET BY HPEXT IS .0 
DESIGN PRESSURE RATIO FOR COMPRESSOR COMPONENT NUMBER 2 SET BY FPRDES IS 1.56 
DESIGN PRESSURE RATIO FOR COMPRESSOR COMPONENT NUMBER 4 SET BY OPRDES/FPRDES/HPC 
PR IS 1.54 
DESIGN PRESSURE RATIO FOR COMPRESSOR COMPONENT NUMBER 5 SET BY HPCPR IS 11.50 
MAXIMUM ADIABATIC EFFICIENCY FOR COMPRESSOR COMPONENT NUMBER 2 IS .8988 
MAXIMUM ADIABATIC EFFICIENCY FOR COMPRESSOR COMPONENT NUMBER 4 IS .8990 
MAXIMUM ADIABATIC EFFICIENCY FOR COMPRESSOR COMPONENT NUMBER 5 IS .8558 
JPS-OUT 
DESIGN BURNER TEMPERATURE SET BY TETDES IS 2572.0 
# CONFIGURATION DATA 
16 STATIONS, 25 COMPONENTS. 
COMPONENT NKIND COMPONENT 
NUMBER TYPE 
UPSTREAM 
STATIONS 
DOWNSTREAM 
STATIONS 
1 1 INLET 1 0 2 0 
2 4 COMPRESR 2 0 3 0 
3 7 SPLITTER 3 0 4 12 
4 4 COMPRESR 4 0 5 15 
5 4 COMPRESR 5 0 6 16 
6 2 DUCT B 6 0 1 0 
7 5 TURBINE 7 16 8 c 
8 5 TURBINE 8 15 9 0 
9 2 DUCT B 9 0 10 0 
10 9 NOZZLE 10 0 11 0 
11 2 DUCT B 12 0 13 0 
12 9 NOZZLE 13 0 14 c 
13 11 SHAFT 5 7 14 0 
14 IC LOAD 0 0 C 0 
15 11 SHAFT 2 4 8 0 
16 12 CONTROL 10 0 8 0 
17 12 CONTROL 8 0 7 0 
18 12 CONTROL 7 0 5 0 
19 12 CONTROL 5 0 4 0 
20 12 CONTROL 4 0 2 0 
21 12 CONTROL 2 0 1 0 
22 12 CONTROL 13 0 3 0 
23 12 CONTROL 13 0 13 0 
24 12 CONTROL 15 0 15 c 
25 12 CONTROL 0 0 1 0 
* CONTROL INFORMATION 
16 VARY CDAT 1 OF 
.O00OOE+OO 
17 VARY CDAT 1 OF 
.00OO0E+0O 
18 VARY CDAT 1 OF 
.000O0E+00 
19 VARY CDAT 1 OF 
.OOOOOE-i-OO 
22 VARY CDAT 1 OF 
.00O0OE+00 
20 VARY CDAT 1 OF 
.00O00E+OO 
21 VARY CDAT 1 OF 
.OOOOOE+00 
2 5 VARY CDAT 1 OF 
.10000E+05 
23 VARY CDAT 1 OF 
.OO00OE+O0 
24 VARY CDAT 1 OF 
.O0OO0E+O0 
* DESIGN OUTPUT SUMMARY 
ALTITUDE MACH FN 
T9 PR9 A9 RR 
0. .000 56750. 
1185. 1 1642 1.000 
COMPONENT 8 SO THAT STATP B OF FLOW STATION 10 EQUALS 
COMPONENT 7 SO THAT STATP 8 OF FLOW STATION 8 EQUALS 
COMPONENT 5 SO THAT STATP 8 OF FLOW STATION 7 EQUALS 
COMPONENT 4 SO THAT STATP 8 OF FLOW STATION 5 EQUALS 
COMPONENT 3 SO THAT STATP 8 OF FLOW STATION 13 EQUALS 
COMPONENT 2 SO THAT STATP 8 OF FLOW STATION 4 EQUALS 
COMPONENT 1 SO THAT STATP 8 OF FLOW STATION 2 EQUALS 
COMPONENT 1 SO THAT NET JET THRUST (LBS) EQUALS 
COMPONENT 13 SO THAT DA TOUT 8 OF COMPONENT 13 EQUALS 
COMPONENT 15 SO THAT DATOUT 8 OF COMPONENT 15 EQUALS 
8SHP WF SFC R FLOW BPR BOT T19 PR19 Al 9 
NIT V9 AEXIT 
0. 19379. .341 1995.9 4.000 2572. 600. 1.515 3447. 
5 988. 1921 
STATION PROPERTY OUTPUT DATA 
Km 18% 
15:07:49 B747-FLOPS-OUT 
FLOY. MEIWHT TOTAL TOTAL 
MACH STATIC INTERFACE RELATIVE 
STATION FLOW PRESSURE TEMPERATURE 
UMBER PRESSURE FLOW EHRQR 
STATPl STATP2 STATP3 
TATP6 STAT P 7 STATE*B 
1 .1995JE+04 . ".J696E+02 .
 r,i^67E-03 oOOoe+dg- . oooDORt;;:- . ooooOe+oo 
.L9959E-D4 .I469&E+02 .51867E+03 ocpnr.no .oooooe+cc . ;>:•::•:•:•£+-:••. 3
 .19959E+04 .2292«E*D2 .599822+03 ooooe+oo oooooe+oo .oooooe+oo 4
 .IrPiBEfO.l .22BI3E+02 .5996JE+03 ooooe+oo .oooooe+oq . ooccoe+qo 
5 .3991liE + 03 -35221J?>r!2 .69O76E+03 ooooe+co .oooooe+od .oooooE+on 
6 .2974&K+03 .105U(EiC3 .146B0E+04 OOOOE+OO .00QD0E+OO .OOOOOE+OO 
7 .302£4E*O3 .4009SE+03 .25720S+04 QOCUE+OO .0OO0OK+00
 .O000DE+00 
8 .40457B+03 .76141E+02 .16269E+04 OOOOE+OO . 0OD00E+.O0 .OOOOOE+OO 
9 .40»dVE-U3 .iaaa7E+02 .11S51E+04 
O000E+0O .O0000E+O0 .OOOOOE+OO 10
 .40457E+O3 .18887E+02 .11851E+U4 
1486E+QO .14C9.GF+Q3 .UOOOOE-GQ 1
 .40457B+0J .188B7E+02 ,11E51E+04 
1179E+00 .14696E*02 .OD000E+00 
12 -15967E+04 .2J490E+02 .59983E+03 
OO0OE+00 .000O0E*O:' .QOuDOb+OO 
i', .l'ji!67E + 0i . 222 65E+02 .59983E+03 5>2BlHoO .14696E+02
 . OOuOUE+OL 
14 . l'.s367E+04 .222S5E+02 . S999JE+03 
8884E + 00 .14696E+02 .QQOOOE+CO 
15 .OOOOOE+OO .OOOOOE+OO .0OO0OE+00 OOOOE+DO
 .OOOOOKtOO . O'Jl'OOE+Oi, 
16 .LO173S+0" .40504E+03 .1468OE+04 ooooe+oo . oooooe+ou .oooooe+oo 
FUEL/MR 
RATIO 
STATP4 
.OOOODEhQO 
.O0O00E+00 
.000055*00 
.OOQOCE+CO 
.O0O00E+O0 
. OCOOOE-OO 
. 190'.>7E-Ol 
.134B5E-01 
.13485E-0I 
.13435E-01 
.13485E-01 
.OOOOOE+OO 
.O000OE+O0 
.O0O00E+00 
.000003+00 .OQOOOE+OD 
COMPONENT OUTPUT COMFOMENT NO. TYPE DATOUTl DATOUT2 DATOUT3 ATOIJT6
 DATOLT7 DATOUTB DATOUT3 
1 INLET .OOOOOE+OO .ODOOOE+00 .009C0E+OO qoooe-oo .loooiit-.. i .iooooe+01 oooooe+oo 
i CCMFRESR -.553O9K+05 .1O00OE+01 .OOOOOE+OO 
7OO0E+D0 .76B&5E+01 .S6405E+00 .15600E+Q! 
3 SPLITTER .40000E+Oi .5OU0UE-02 .19000E-O1 ooQQE+tfQ . oooooe+oo . oooooe+oo .oooooe+oo 
4 CdMPRftSH - . 12 J72.E+05 .1O000E+01 .OOOOOE+OO jCOOEiOO
 .110BJE+0I .S7039E-Q0 . 154SUE+01 
5 EQHEflJgSB H03BE + 06 .IOOOOE+01 .OOOOOE+OO 
500DE+00 .141156*01 .64.BO4E-0O .11500E+02 
6 DUCT D .OOOOOE+OO -lOOOOE-Ul .OOOOOE+OO 
9379E+05 .OOOOOE'OO .10500E+O5 
7 TURBINE . ] ) P-3 Bj"+06 . 10000 E* ooooE+oi ,aay36E+oo .89oode+co 
8 TURBINE .673R13+0S .10000E+ 
"J. 99 0O0E+OO Ui .0' 100] .52664E+0T 0  .OfilOOE + 00 
.40313E+01 DD00E+D3 . 4976JEH-01
 .90000Et00 9 duct b .oooooe+00 .oooooe+00 .oo000e+0o ooooe+oo .oooooe+oo .issooe+ds .oooooe+oo 
10 NOZZLE .12426E<Di .9aa23E+03 .16424B+04 9800E+00 .9950OE+00 ,OOOOOE+OO .1285ZE+01 1  DUCT B .OOOOOE+OO .10000E-01 .OOOOOE+OO OCOOF+OC .OOOOUEiOU .1B500E-05 .OOOOOE+OO 
12 NOZZL  .44">24E + 05 . 39.1 : •• ii • )3 .3-1472E+04 
DAT0UT4 
.lOOOOEiOl 
.22DOQE+01 . OD</OL3K+00 
.19500E+01 
.19500E+01 
.18097E-01 
.300002+01 
.30000E<01 
.OOOOOE+OO 
. 99319E+03 .OOOOOE+OO 
.89761E+03 
REFERRED 
FLOW 
STATPi 
,13959E-0( 
.19959E+04 
•13755EI04 
.27656E+03 
•19221E+03 
.18157E+02 
.24715E+02 
.13829E+03 
.475B3E+Q3 
.475*3E+03 
.475S3E+03 
.11220E+04 
.11334E+04 
.11334E+04 
.0000,. ,00000E+O0 
DATA 
DATOUT5 
.10000E+01 .19434B102 
.OOOOOE+OO 
.16B16E+02 
. 1P42 i V. t02 
,OOOOOE+OO 
.23093E+04 
.1S269E+04 
.OOOOOE+OO 
.16424E+04 
.OOOOOE+OO 
.34472E-04 
N S 
. 0 .0 
.0 
. o .0 
.0 ,0 
.0 . 0 
. 6 
.6 . 0 
.7 
, 7 . 0 
. 0 
D .0 
.5 . 0 
.9 . 9 
. 1 
.1 
. 1 . 0 
.9 . 0 
. 9 
t >5D0E+00 .99500E+O0 .OGOOOEtOO .15I51E+01 
13 SHAFT .DOOOQErOO .1000UE+01 .l^OCOE-Dl 
+ 0050E+QQ .OOOOOE+OO .OOOOOE+OO .OOOOOE+OO 
ii U^AD .OOOOUE+00 .IDPOOE+OJ .OOOOOE+OO 
* (100dH*0O .DDDPOE+00 .O0O0UE1OO .OOOOOE+OD 
15 S:'.n.FT .OOOOOE+OO .j.OOOOE+01 .lOUOUE+01 + ooooe+oo .oooooe+oo .oooooe+oo .ooocqe+oo 
PERFORMANCE OUTPUTS 
.lOODDE+Oa . OOOOOE+OO 
. IOOOOE+01 
MACH 
0 . FT 
(1) NET JET TMRUET (LBS] 
{3> AIRFLOW (LE^SEC) 
[*) TSFC (LB/HK/LBJ 
(0) FUEL FLOW (LE/HR) 
(7) NET THRUST/AIRFLOW 
(91 TOTAL CfLWi (LPS) 
567M.QC 1995.91 19378.55 
23. 43 .00 
(2) MET BRAKE SHP 
(5) BSFC (LB/RR/HP) 
(8) NET BSHP'AIRFLOW 
5 tr-W-.TIONS 14 
.IOOOOE+01 .0 
.oooooe+oo ,o 
•IOOOOE+01 .0 ,000 / ALT = 
.00 .oooo 
.c TURBINE COOLING AIRFLOW COMPUTED AT 25.48%. 
# COMPRESSOR COMPONENT NUMBER 2. 
WARNING - BLADE CENTRIFUGAL STRESS FCH COMPRESSOR 7. HAS SEEN EXCEEDED. 
COMPHaaSOft Til' SPEED WILL DE INDUCED TO 1119.6 ; i/SEC ;OR A HUB TO TIP 
+ z m : • oc 
DESIGN PARAMETERS 
DESCRI P'J-JON NAHE VALUE 
MASS FLOW WTFWT 1994'. 91 
STAGE FLOW ANGLE ALFI 23.6390 
DIFFUSION FACTOR DTFFF .600000 
POLYTROPIC EFFICIENCY PEFF .B7231 
IGV ENTRAUCE NACH XMO .50000 
SOLIDITY SIGMA 1.00000 
HUH TO TIP RADIUS RATIO FJJ2T .35000 
REOOIflElt PRESSURE RATIO SEQPR 1.5E0DO 
TIP SPEED UT IJ.19 - 64 
ROTOR ENTRANCE MACH XMEF ,57000 
I'.j MENS I ON 
L.B/SEC 
DEG 
FT/SEC 
STAGE MATERIAL DENE I TV .0980,
 USABLE STRESS HOB RAH I US TIP RADIUS TOTAL TOTAL Al OLE MACH PRESSURE WEIGHT DENSITY'TEMP STAGE/rffl (IN) (IN)
 TEE? !R) PRES (PST) '"': EG) NUMBER RAT]0 (LB) (LB/CI)/(R) 700. : IN) AN (D 
1 / 45 .570 IS. 60 •.• . i 1.55 3227. 599 . 1 .0980/ 672. 2  .81 7734.37 TOTAL = 1227. 
RESULTS AFTER S5 ITERATIONS 2 
EAXTMUM AN = 
ROTATIONAL SPEED = ROTATImjAL
 SPEED 
TIP SPEED 
KEAW RADIUS 
HAJtlHUH RADIUS 
ASPEC1' RATIO, FIRST / LAST = 
10 
•S X 10 
252.84 
2414.4 
111S.64 
35.87 
53 .14 
5-00 
)N-RPM 
RAD/S EC 
FT/SEC IN 
'5.00 
15:07:49 
RDTOR INLET HEL 
LENGTH 
vn • Gi R 
(f COWPRBSSCP COMPONENT NUMBER 
E- rnN U1ETERS 
DESCRIPTION 
M71SS FLOW 
STAGE FLOW ANGLE 
DI FPUS J ON FACTOR 
POLVTROWC EFFICIENCY 
IGV ENTRANCE MACH 
SOLIDITY 
HU3 TO TIP RADIUS RATIO 
REQUIRED PRESSURE AA'flQ 
TIP SPEED 
ROTOR ENTRANCE MACH 
47- FLOPS-OUT 
NAME 
WTFWT 
ALF1 
I. .[••!•• V 
PEFF 
XMU 
SIGMA 
RFI2T 
(tlCPR 
UT 
XMEF 
.8497 
15. OC 
I22t .88 
VALUE 
399 .18 
5.7723 
554319 
.87809 
.500C0 
.00000 
.66936 
.54404 
S58.51 
. 57000 
IN 
LB 
DIMENSION 
Lil/SEC 
PEG 
FT/SEC 
1 - MATERIAL DENSITY = . 1430, 
HUB RADIUS 
GLE MACH PHES^UH! 
STAGE/NB (IN) 
EG) NUMBER RATIO 
USARl.S STRESS 
TOTAL IP RADIUS TOTAL 
WEIGHT DENSITY/TEMP 
(IN) TEHP (R) PRES (PSI) 
(LU) (LB/CI)-<R) 
45000, 
AREA 
fIN'IN) 
AN 
(D 
1 
. 77 
89 17.74 
.570 1.54 
2* .51 
275. 
689.6 
.1430/ 773. 
35 
TOTAL - 2 7 5. 
'tESl'LTS AFTER 63 ITERATIONS 
2 
MAXIMUM A N 
ROTATIONAL SPEED 
ROT ATIONAL SPEED 
TIP SPEED -
MEAN RADIUS = 
MAXIMUM RADIUS 
ASPECT RATIO, FIRST / LAST I 
ROTOR INLET RSL MACH ND. = 
LENGTH = 
WEIGHT
If TURBINE COMPONENT NUMBER 
DESIGN PARAMETERS 
10 
.710 X J0 
252.84 
2414.1 
558.51 
22 . 13 
26.51 
5.00 / 5 
.8511 
9.29 
274.59 
2 2 
IN- RPM 
RAD/SEC 
RPM 
FT/SEC 
IN 
IN 
00 
IN 
DESCRIPTION NAME VALUE DIM! 
MASS FLCW UTFWT 404.57 LB/f 
STftTOR ENTRANCE MACH XHIIM .6O000 
NOMINAL ROTOR MACH XH.2 IN 1.00000 
RE0UE5TEU EXIT SWIRL ANGLE ALF3E . 0000 DEG 
AXIAL VELOCITY RATIO U1U2 1.20000 
INLET TOTAL TEMPERATURE TTWT 1626.H5 R 
IHTPR TOTAL PRESSURE PTUT 7 6. •: PSR 
EXIT TOTAL TEHCEJtATUPE TTEX 
LIAS. n 
R 
""DEL TO AIR RATIO VASWT .0134E5 
ROTATIONAL SPEED RPM 2. . .4 RPM 
KAXIMUM RADIUS RTMAX 40.412 IN 
INITIAL MEAN RADIUS 26.184 IN 
+ S RAM I US 
+ N) HUB I IN) 
TOTAL STATIC TOTAL STATIC 
AREA 2" 
TEMP (E) TEMP (Rl P (PSI) P ( ) 
UN* IN) A*N 
HACH ALPHA RADIU 
NUMBER (DEG) TIP (I 
5TATOR INLET 
0 21.674 
ROTOR INLET 
0 2 2.303 
1626,85 153J.27 76.141 60,258 
487.5 .28421E10 
1626,85 1336. 11 74. 0.20 39.986 
1266.6 .7381BE10 
50.566 ROTOK EXIT J479.61 1436.45 
' 3 ii,2iu 961.9 .56074H10 
I STAGE WT = 972. LBS; ROTR EXIT REL. MACH NO. 
+ 3; 52 RO TR AND 63 STATR BLADES I 
.6000 
1.0000 
4-"I, ICS .37 19 
= .53 8; DEGREE LV 
STAGE - 2 -
* S RADIUS 
+- N) HUH LIE) 
MATERIAL DENSITY 
TOTAL 
."."•• ^ 
TEMP (R) 
TIN* IN) 
TESHf (R) P (PSI) 
A*N 
960, '. .".••• STRESS = 30000 . 
TOTAL STATIC MACH 
P (PSI) NUMBER 
.000 
70 .739 
10.067 
REACTION 
ALPHA 
(I7ER;) 
27 . 64 
30.01 
29 . OS 
= -.34 
RADIU 
TIP (I 
Si/.:- 1479.61 1 140.9-; 
ROTOR INLET 1479.61 1256.45 
+ 4 76.31:1' 3220.2 1.87719E10 
ROTOR EXIT 1.332.77 1316.4/ 
+ 8 13.556 2363.6 1 ,37785E10 
( STAGE WT -3 6SS . LBS; SIOTR EXIT REL 
+ 8; 27 ROTR AND 33 STATR iiiiADES I 
50.566 
49.419 
32.700 
45.597 
26.486 
31.236 
.3949 
1 . ODDO 
. 2257 
10.067 
79 .?aa 
15.001 
•M NO. = .432, DEGREE OF REACTION 
29 . 08 
35.95 
33.34 
- -.40 
STAGE - 3 - MATERIAL DENSITY = .1430, USABLE STRESS = 27549. 
TOTAL STATIC MACH ALPHA RADIU 
P IRE'L NUMBER I DEG) TIP (I 
+ S RADIUS 
+ N) HU3 UN) 
TOTAL 
ARJ . , 
TEH? (R) 
(IN*IN) 
STATIC 
2 
TEMP (R) P (PSI) 
A'N 
STATOR INLET 
8 1ft.965 
ROTOR INLET 
6 21.168 
RO -i T'XIT 
0 21.433 
(STAGE WT = 
1332.37 1320.5S 
2363.8 1.37797E10 
17.32.37 1127.12 
1639.9 .95501E1O 
11B5.13 10H7.77 
1559.2 .90894E10 
525. LBS; PCTR EXIT REL. MACH NO. 
32.700 
31.957 
19.BIO 
3;. 539 
17.082 
14.361 
.2257 
1 .0000 
. 6952 
MATKR3AL DENSITY USA? 
0; 53 ROTR AND 64 STATR BLADES) 
RESULTS AFTER 42 ITERATIONS 
2 
MAXIMUM A N 
ROTATIONAL SPEED 
RJI'AT'IONAIH SPEED 
MEAN RADIUS 
MAXJNI7M RADIUS = 
LENGTH 
WEIGHT 
# COMPRESSOR COMPONENT NUMBER 5. 
WHINING - MAXIffliM W!iEEL SPEED FOR COHPHgSSOjX 5 HAS BEEN EXCEEDED. 
tOMFRESTSCR TIP SPEED WILL BE REDUCED TO 1122,1 FT/SEC FOR A HUE TO TIP 
RADIUS RATIO OF .7104. 
. S77 X 10 
2j2.84 
2 414 , 4 
26 .16 
30,90 
31.84 
7'76.52 
.876; DECREE 
2 2 
IN-RPM 
RAD/SEC 
RPM 
IN 
HJ 
. N 
LJ 
15.001 33,30 
57.573 3T-LI 
20.000 30.90 
XKACTIOH = -27 
B747-FLOPS-OUT 
DESIGN PARAMETERS FUF-L TO AIR RATIO FAS.WT ,0lBO»7 
DESCRIPTION 
NAM IF VALUE DIMENSION ROTATIONAL SPEED RPM 5541.4 
MASS FUOW WTFWT 339 IS LB/SEC MAXIMUM RADIUS RTKAX 40 .6.12 IN 
STAGE FLOW ANGLE 
ALF1 34 .8434 •EG INITIAL MEAN RADIUS RM 
2 c .772 IH DIFFUSION FACTOR DIFFF .554315 PPLYTROPIC EFFICIENCY JPEFF .89006 STAGE - 1 - MATERIAL DENSITY - 2960, USABLE STRESS = 15000. 
IGV ENTRANCE MACH M-iO .5OO0Q 
SOLIDITY SJfGlffi 1.00000 TOTAL TOTAL STATIC MACH ALPHA 
HUB TO TIP RADIUS RATI'i 
RH2T .71044 S RADIUS AREA 2 
Kl-.v'..U.-»Kr> PRESSURE rati:' RFXjHR 11.50 0 T.-1K: •:- • TEH? (R) P (P.ST) P (PSI) NUMBER (DEG) TIP SPEED UT 2 . 13 FT/SEC + N) HUB (IN) (IN*IN) H' N HC.-r ~. • "ACH XMEF .57000 4 
STAGE - 1 - MATfcftJAL DENSITY = 29 60, USA&fJv .STRESS = 30000. STATOR INLET 2309.2B 2187.45 400.993 318.806 . 6000 .ooo 
+ 0 22.445 111.3 .34178E10 
HUE RADIUS TIP RADIUS '1 J'I'AI TOTAL AREA 7 AN ROTOR INLET 2309 . 2B 1991.45 391.971 211. 5 J :', 1.0053 59.970 
GLE MACH PRESSURE WEIGHT DENS ITY/TEH I* + 6 ,'.2.169 190.4 .5S475E10 
MAGE/NB (IN) (IK) TEMP (R) PRES (PSI) (IN*TN) A*K ID ROTOR EXIT 1968.06 1340.43 192 . 5^7 145.628 . 6568 17.029 
EG] NUMhLK RATIO 1 LB) 
(LB/ ii/<r) + 
0 22,0S« 
211.7 .6502.' El* (STACK WT 
TOO. LBS; ROTO EXIT REL.. MACH NO. = .966; DEGREE OF REACTION 
R AD I' J 
TIP (I 
/ 54 IC . 43 23. n 792 . 1 54 23 837 79 2 57263E10 34 5 
',7 0 1 . 54 230. .1130/ 888. 
2 / 64 17 .IS 22 .30 B93 .6 79 19 612 33 1 88U31E10 34 
.84 530 2 . 25 132 . .1430/1000. 
3 / 74 
•15 3 
17 .9f 
3 . 15 
21.71 
93 . 
»*3 .3 
.1430/1109. 
110 94 466 05 43112E10 34 
4 / ?.=> io .36 21 . ji lual.5 ] 5U 36 365 BS 1 1I353E10 34 
. S4 471 4 .27 80 . .1430/1217. 
18 . 66 21 . 03 1.188.1 198 33 294 31 90374E10 34 
. • " 448 5.63 73 . .1430/3322. 
/103 18 . 88 20 .81 1203.2 255 79 241 38 74!21E10 34 
. ' 4 429 7.26 93 . .J430/I4i«. 
7 /ill 19 .04 20. 65 1376.9 323 69 201 15 61769F.10 34 
BI 412 9 . 19 
19 j . .i^60/1527. w /H9 19 .16 2.0 . 53 14*9.1 403 04 169 89 52170E10 34 .84 39B 11.44 ltd . .2360/1627. 
3; 12s! Ko'l'R ANL> I"-5 oi'ATR BLADES) STAGE -
 2 - MATERIAL DENSITY = 
+ S RADIUS * N)
 HUB (IN) 
TOTAL 
AREA 
TEMP 1R) 
I WIN) 
STATIC 
2 
TEMP (RI P IPSII 
A*M 
2960, USABLE STRESS = 22435. 
TOTAL STATIC MACH 
P (PSI) NUMBER 
23 , 22 
23 .49 
23 .57 
= . 44 
ALPHA RABID 
(DEG) TIP (T 
ST. " INLET 
* 0 22.094 
ROTOR INLET 
+ 8 21.307 
ROTOR EKET 
+9 21.10€ 
TOTAL - 1083 . 
RESULTS AFTER 49 ITtHATjONS 
2 
MAXIKUM A N 
E0TATIOMAL 3PEE0 
ROTATIONAL SL'EED 
TIP SPEED 
MEAN RADIUS 
MAXIMUM. PAPIUS 
ASPECT RATIO, FIRST / LAST 
ftPTOR INLET REL MACH NO. 
LENGTH 
WEIGHT 
S TURBINE COMPONENT NUMBER 7 . 
DESIGN PARAMETERS 
DESCRIPTION NAME 
MASS FLOW WTFWT 
STATOR ENTRANCE MACH XM1IN 
NOMINAL ROTOR MACH XH3tN 
REQUESTED EXIT SWIRL ANGLE ALF3E 
AXIAL VELOCITY RATIO U3U2 
i.NI IT TOTAL TEMPERATURE TTWT 
IULET TOTAL PXASSURE PTWT 
EXIT TOTAL TEMPHHAI'JHS TTEX 
10 
2 . 573 X 10 
560 .30 
5641.4 
1122.13 
19.05 
23 .20 
2 .57 
.5923 
27 .71 
1083.40 
VALUE 
4 04.57 
.£0000 
1 .03000 . oooo 
1 .20000 
2309.28 
400.99 
1626.B5 
2 2 
IN-RFH 
RAD/KFC 
RPM FT/SEC 
IN 
IN 
/ 1 .29 i,: 
I 7. 
ITMKN.S'I OH 
If'oli.Of; 1840.3 9 .'ill.7
 . 65OZ2E10 
1968.06 K-*6.9S 
437.3 1.34434E10 11)26.85
 1544.33 
495.4 1.53119610 
(STAGE WT •- 398. ITS; ROTR EXIT REL 
80 F.OTR AND 9 6 -S'CATR BLADES) 
192.557 
188.192 
83.371 
146.171 
100.885 
67 . 538 
. S 5 6 8 
1,0074 
. 5628 
,946; DEGREE OF 
17.029 23.57 
65.343 24.35 
20.514 24.55 HFACTION = .41 
RESULTS AFTES 345 ITERATIONS 
2 
MAXIMUM A N 
ROTATI :• SPEED 
ROTATIONAL SPEED 
MEAN RADIUS 
MAXIMUM RADIUS I.BW 
WEIGHT 
LMHPRESSOR FRAME WEIGHT 
TURBINE FRAME WKr'D'T 
10 
.521 X 10 
580.30 
5541.4 
22 . 83 
24.56 
7 . 13 
1097.39 
2 2 
IN-RPM 
PAD/SEC 
RPM 
IN IN 
IN 
LP-
DEG R 
p.7;:. K 
* SPLITTER C'-MPONENT NUMBER 3. 
DESI0W PARAMETERS (PRIMARY 
DESCRIPTION 
MASS FLOW 
INLET TOTAL PRESSURE 
FJIT TOTAL TEMPERATURE 
FUEL TO AtR RATIO 
BYPASS DUCT HASS PLOW 
BYPASS DUCT MACii NUMULR 
RESULTS 
WALL THICKNESS SPlj • -..I • TH 
TREAM) NAME WTFWT PTWT 
:• TWT FARWT 
WTFSEC xmach 
906. "S3 LB 
487.68 L'S 
VALUE 1)1MENSION 
', 9J/S.9] LB / SEC 
22.91 PSI 
599 . 0 DEG fi 
.00000 
1536.72947 LB/SEC 
.52806 
. LD0OC TTI 
3.34 ;n 
Nov 18 96 
15:07:49 B747-FLOPS-OUT 
SPLITTER WEIGHT 
HP-LP TURBINE DUCT WEIGHT 
# BURNER COMPONENT NUMBER 6 . 
DESIGN PARAMETERS 
DESCRIPTION NAME 
MASS FLOW WTFWT 
INLET TOTAL PRESSURE PTWT 
EXIT TOTAL TEMPERATURE TTWT 
FUEL TO AIR RATIO FARW
INLET MACH NUMBER XMACH 
RESULTS 
AREA RATIO (EXIT/REFERENCE) 
OUTER DIAMETER 
INNER DIAMETER = 
OUTER WALL THICKNESS 
BURNER LENGTH
TOTAL LENGTH = 
BURNER WEIGHT 
FRAME WEIGHT = 
TOTAL WEIGHT 
HP-LP TURBINE DUCT WEIGHT = 
TOTAL BARE ENGINE WEIGHT1 
9.63 LB 
13.85 LB 
INLET 
297.46 
405.04 
1468.0 
.00000 
.09481 
EXIT 
302.84 
400.99 
2572 .0 
.01810 
DIMENSION 
LB/SEC 
PSI 
DEG R 
.224 
45 .14 
40.21 
,20000 
20.07 
25.13 
984.17 
502.42 
IN 
IN 
IN 
IN 
IN 
LB 
LB 
1486.59 LB 
70.90 LB 
11854.38 LB 
INITIALIZE CRUISE THERMODYNAMIC AND PERFORMANCE DATA AT MACH NUMBER 
+ UDE = 39000. FT. 
BPR BOT ALTITUDE MACH FN BSHP WF SFC R FLOW 
T9 PR9 A9 RR NIT V9 AEXIT 
39000. .850 10498. 0. 6803. .648 2183.5 3.838 2396. 
1045. 2 1642 1.000 1 1436. 1646 
(t WEIGHT AND DIMENSION SUMMARY 
T19 
531 . 
NACELLE WEIGHT AND DIMENSION SUMMARY 
+• WT/A THICKNESS 
+ (PSI) (IN) 
INTERNAL SURFACE OF COWL TO ENGINE 
+ 02352 .080000 
EXTERNAL SURFACE OF COWL TO ENGINE 
+ 02352 .080000 
EXTERNAL SURFACE FROM ENGINE TO FAN NOZZLE 
+ 02352 .080000 
EXTERNAL SURFACE FROM ENGINE TO NOZZLE 
+ 02352 .080000 
CORE NOZZLE 
+ 02145 .050000 
PAN NOZZLE 
* 02352 .080000 
TOTAL 
NACELLE WETTED AREA 
NACELLE LENGTH (EXCLUDES SPIKE) 
INLET WEIGHT 
NACELLE WEIGHT 
CORE NOZZLE WEIGHT 
FAN NOZZLE 
WEIGHT 
(LB) 
374.0 
446 .4 
135.6 
516 .4 
117 .5 
853 .2 
970. 6 
LENGTH 
(IN) 
49 .5 
49 . 5 
15.1 
116.7 
27 .9 
104 . 7 
209 .2 
.85, ALTIT 
PR19 A19 
2.569 3447. 
AREA 
(SQIN) 
15899. 
18978. 
5767 . 
21956. 
5476, 
36274. 
61019. SQ.IN. 
209.2 IN, 
374.0 LB 
1098.4 LB 
117.5 LB 
853 , LE 
INLET CAPTURE RADIUS 
EBU + CONTROLS + ETC. 
JET VELOCITY WEIGHT PENALTY 
INLET WEIGHT (+MOUNTS, ETC.) 
NOZZLE WEIGHT 
ENGINE WEIGHT 
TOTAL PROPULSION SYSTEM WEIGHT 
45.0 IN 
3574.3 LB 
. 0 LB 
1472.4 LB 
970 . 6 LB 
11854,4 LB 
17871.7 LB 
# MACH - ALTITUDE POINTS 
WHERE PROPULSION PERFORMANCE DATA WILL BE COMPUTED. 
AT MACH = ,850 THE 2 ALTITUDES ARE 
39.OK 35.OK 
AT MACH = ,600 THE 2 ALTITUDES ARE 
20.OK 15.OK 
,000 THE 2 ALTITUDES ARE 
4.OK ,0K 
OFF DESIGN POINT DATA FOLLOWS 
» DATA AT MACH 
ALTITUDE MACH 
55, 39000. FT 
FN 
T9 
39OO0 
1045 . 
39000 
1009 . 
39000 
975. 
39000 
952 . 
39000 
930 . 
39000 
908 . 
39000 
888. 
3 9OO0 
868, 
39000 
849 . 
39000 
831 . 
39OO0 
B13 , 
39000 
796. 
39000 
780. 
39000 
765, 
39000 
750. 
PR9 A9 RR 
.850 10498. 
? 1642 1.000 
,850 9510. 
1642 1.000 
.850 8579. 
1642 1.000 
.850 7929. 
1642 1.000 
.850 7252. 
1642 1.000 
.850 6588. 
1642 1.000 
.850 5946, 
1642 1.000 
.850 5308. 
1642 1.000 
850 4695. 
1642 1.000 
.850 4128. 
1642 1.000 
850 3600, 
1642 1.000 
850 3081. 
1642 1.000 
850 2590. 
1642 1.000 
850 2127, 
1642 1.000 
850 1682. 
1642 1.00C 
# DATA AT MACH .85, 35000 
ALTITUDE MACH FN 
T9 PR9 A9 
35000. 
1056 . 
35000. 
1021. 
35000. 
RR 
.850 12725. 
2 1642 1.000 
.850 11527. 
1 1642 1.000 
,850 10399. 
BSHP WF SFC 
NIT V9 AEXIT 
0. 6803 . .648 
1 1436 . 1646 
0. 6155, , 647 
B 1405. 1642 
0 , 5550. . 647 
2 1310 , 1648 
0. 5142. . 649 
14 1245 . 1658 
0 . 4743 . . 654 
17 1179 . 1675 
0. 4361 . .662 
8 1115 . 1698 
0. 3999 . . 673 
2 1052, 1728 
0, 3652 . .688 
2 990 . 1766 
0. 3325. .708 
2 930 . 1813 
0 . 3021. .732 
2 573 . 1867 
0. 2738 , ,761 
4 318, 1929 
0, 2472 . .802 
3 765. 2001 
0 . 2221. .858 
3 713 . 2085 
0. 1984 , .933 
2 662 , 2185 
0 . 1764 . 1 .049 
3 614 . 2299 
. FT 
BSHP WF SFC 
NIT V9 AEXIT 
0. 8296. .652 
1 1444 . 1646 
0 . 7505. . 651 
e 1414 . 1642 0. 6767 , .651 
R FLOW 
2183.5 
2136.2 
2089.9 
2054.7 
2014 .2 
1972 .0 
1929.1 
1883.5 
1837.6 
1793 .4 
1750.6 
1706.1 
1662 .0 
1618.5 
1574 .3 
R FLOW 
2183.6 
2136 . 4 
2090.1 
BPR BOT 
3.838 2396 , 
3.984 2322. 
4.140 2248. 
4.251 2195. 
4.368 2143, 
4.491 2090, 
4 . 623 2038. 
4.762 1935. 
4.911 1933. 
5.068 1880, 
5.233 1828. 
5.405 1775. 
5.601 1723. 
5.828 1670. 
6.070 1618. 
BPR BOT 
3.838 2419. 
3.984 2344, 
4 .140 2270. 
T19 
531 . 
527. 
522 . 
518 . 
515. 
511 . 
507, 
503 . 
500 . 
496. 
492 , 
489 . 
485. 
481 . 
478. 
T19 
537 . 
532 . 
527. 
PR19 A19 
2.569 3447. 
2.521 3447. 
2.473 3447. 
2.435 3447. 
2.391 3447. 
2.344 3447. 
2.297 3447. 
2.246 3447. 
2.194 3447. 
2.145 3447 . 
2.097 3447, 
2.046 3447. 
1.997 3447. 
1.949 3447. 
1.900 3447, 
PR19 A19 
2.569 3447. 
2.521 3447. 
2 . 474 3447. 
Nov 18% 
| 15:<)7:49 B747-FLOPS-OUT 
986. 1 1642 1.000 2 1318. 1648 15000 .600 22477. 0 . 13602. .605 2070 5 4 .148 2481. 580. 1 946 3447 
3SOO0. .850 9611. 0 . 6269 . . 652 2054 .9 4 .251 2217 . 524. 2 .436 3447. 4 1108. 1 1642 1.000 17 1168 . 1731 
963. 1 1642 1.000 14 1253 . 1658 15000. .600 20646. 0 . 12530. . 607 2025 .6 4 .264 2422 , 575. 1 .906 3447 
350OQ. .850 8792. 0 . 5782 . .658 2014 .5 4 ,3 68 2164 . 520 . 2 392 3447 . 4 1084 . 1 1642 1.000 12 1103. 1767 
940 . 1 1642 1,000 17 1187 , 1675 15000 .600 18879. 0. 11514. .610 198C 1 4 .385 2363 . 571. 1 .866 3447 
35000. .850 7986. 0. 5317. .666 1972 2 4 .491 2111 . 516. 2 .345 3447 . 4 1062 . 1 1642 1.000 12 1040. 1810 
918. 1 1642 1.000 8 1122 . 1698 15000. .600 17145. 0 . 10549. . 615 1932 6 4 509 2304, 566 . 1 824 3447 
35000. .850 7208. 0. 4875 , . 676 1929 .3 4 .623 2058 . 512. 2 297 3447. 1 1040. 1 1642 1.000 2 980. 1861 
897 . 1 1642 1.000 2 1058 . 1728 15000. .600 15409. 0. 9625. .625 1881 5 4 637 2245 . 562 . 1 781 3447 
35000. .850 6435. 0. 4451 . ,692 1883 8 4 .762 2005. 509. 2 246 3447 . + 1019. 1 1642 1.000 2 920. 1921 
878. 1 1642 1.000 2 996. 1766 15000. .600 13761. 0 . 8759. .637 1830 2 4 .771 2186. 557 . 1 738 3447 
35000. .850 5692. 0. 4052 . .712 1837 8 4 .911 1952 . 505. 2 195 3447. + 999. 1 1642 1.000 2 862, 1990 
859 . 1 1642 1,000 2 936. 1812 15000. .600 12232. 0. 7956 . . 650 1780 1 4 907 2126 . 553 . 1 698 3447 
35000. .850 5004. 0 . 3682 . .736 1793 6 5 068 1899. 501. 2 145 3447 . + 979. 1 1642 1.000 5 808. 2067 
840 . 1 1642 1.000 2 878. 1866 15000. .600 10757. 0 . 7203 . .670 1728 6 5 048 2067 . 549 . 1 657 3447 
35000. .850 4363. 0. 3337 . .7 65 1750 7 5 .233 1846 . 497 . 2 097 3447 . 4 959 . 1 1642 1.000 3 755 . 2154 
822 . 1 1642 1.000 4 822. 1928 15000, .600 9346, 0. 6500 . , 695 1676 2 5 193 20O8 . 544. 1 617 3447 
3 5000. .B50 3734. 0. 3012 , . 807 1706 1 5 .406 1793 . 494 . 2 047 3447. + 941. 1 1642 1,000 2 705, 2252 
805. 1 1642 1.000 3 769 . 2000 15000, .600 8065. 0, 5854 , .726 1626 0 5 341 1949 . 540 . 1 580 3447 
35000. .850 3137. 0. 2706. .863 1661 9 5 603 1740 . 490. 1 997 3447 , 4 923 . 1 1642 1.000 3 658. 2359 
789. 1 1642 1.000 3 717 . 2085 15000. .600 6857. 0, 5255 . .766 1575 7 5 494 1890. 536 . 1 544 3447 
35000. .850 2575. 0. 2416 . , 938 1618 2 5 831 1687 . 486. 1 949 3447 . + 905 . 1 1642 1.000 3 613. 2477 
773 . 1 1642 1.000 2 666 . 2185 15000. .600 5604. 0. 4673 . .834 1519 2 5 668 1831 , 532 . 1 506 3447 
35000. .850 2036. 0 , 2148. 1.055 1574 1 6 072 1634. 483 . 1 900 3447 . + 890. 1 1642 1.000 4 568. 2621 
758. 1 1642 1.000 3 617 . 2299 
+ 
150OO. 
B74 . 1 
.600 4478. 
1642 1.000 
0. 
4 
4140. 
525. 
.925 
2780 
1465 1 5 855 1772 . 529 . 1 47C 3447 
DATA AT MACH .60. 20000 . FT 
ALTITUDE MACH FN BSHP WF SFC R FLOW BPR BOT T19 PR19 A19 * DATA AT MACH .00, 4000 , FT 
T9 PR 9 A9 RR NIT V9 AEXIT ALTITUDE MACH FN BSHP WF SFC R FLOW BPR BOT T19 PR19 A19 
20000. .600 22191. 0 , 132S1. . 598 2174 0 3 846 2553. 570 . 2 034 3447 . 4 T9 PR9 A9 RR NIT V9 AEXIT 
1130. 1 1642 1.000 1 1318. 1668 4000. ,000 49017. 0 . 16777. .342 1995 9 4 000 2581. 602 . 1 515 3447 
20000, .600 20149, 0 . 11991, .595 2121 0 3 994 2474 . 564. 1 989 3447. + 1190 . 1 1642 1.000 1 990. 1921 
1096, 1 1642 1.000 9 1227 . 1695 4000 , .000 44921. 0. 15062 . ,335 1916 6 4 092 2502 . 596, 1 473 3447 
20000. .600 18263. 0. 10798. .591 2070 0 4 149 2395 . 558 . 1 945 3447 , + 1162. 1 1642 1.000 10 918 . 2001 
1064. 1 1642 1.000 17 1141 . 1733 4000. .000 40941. 0. 13469. .329 1834 8 4 178 2422 . 590. 1 432 3447 
20000. ,600 16776. D. 9948. . 593 2025 2 4 264 2337 , 553 . 1 905 3447 . 4 1134 . 1 1642 1.000 3 850. 2095 
1041 . 1 1642 1.000 12 1078 . 1770 4000. .000 37712. 0. 12259. .325 1764 3 4 243 2359 . 585 . 1 397 3447 
20000. .600 15341. 0 , 9142. .596 1979 7 4 385 2280. 549 . 1 865 3447 . 4 1113 . 1 1642 1.000 3 796 . 2182 
1019 . 1 1642 1.000 12 1017 . 1813 4000. .000 34665. 0. 11138. .321 1694 7 4 304 2296 . 581 . 1 365 3447 
20000. .600 13931. 0. B376 . . 601 1932 1 4 509 2223 . 545. 1 823 3447. 4 1093 . 1 1642 1.000 3 745. 2279 
998. 1 1642 1.000 2 958. 1864 4000, ,000 31691. 0 . 10090. ,318 1623 1 4 356 2233. 576. 1 333 3447 
20000. .600 12512. 0 , 7641. .611 1880 7 4 638 2166 , 540. 1 779 3447. + 1073, 1 1642 1,000 2 696. 2386 
978 . 1 1642 1.00C 2 899. 1925 4000. .000 28745. 0. 9110 , .317 1548 2 4 398 2170. 572 , 1 301 3447 
20000. ,600 11168. 0 . 6952. ,623 1829 1 4 772 2108 . 536 , 1 737 3447 . 4 1054. 1 1642 1.000 3 650 , 2 507 
959. 1 1642 1,000 2 843 , 1994 4000. .000 25990. 0, 8209 . .316 1474 4 4 430 2107 . 568 . 1 271 3447 
20000. .600 9922. 0. 6313 . . 636 1778 8 4 909 2051. 532 . 1 696 3447 . + 1036 . 1 1642 1.000 3 607 . 2637 
940, 1 1642 1.000 5 790 . 2071 4000 . .000 23415. 0. 7377 . .315 1401 7 4 456 2044 . 564 . 1 243 3447 
20000, .600 8717. 0. 5714 . . 656 1727 0 S 052 1994 , 527 . 1 655 3447. 4 1017 . 1 1642 1.000 1 565 . 2782 
921 . 1 1642 1.00C 3 738. 2159 4000. .000 20977. 0. 6612 , .315 1328 9 4 468 1981. 560 , 1 217 3447 
20000. ,600 7570. 0 . 5156. , 681 1674 5 5 197 1937 . 523 , 1 615 3447 . 4 998. 1 1642 1.000 3 526, 2939 
904 . 1 1642 1.000 4 689 . 2257 4000 . .000 18525. 0. 5878. .317 1250 1 4 482 1917. 556. 1 191 3447 
20000. .600 6530. 0. 4644 . .711 1624 4 5 345 1879. 520. 1 579 3447 . 4 981. 1 1642 1.000 4 487. 3127 
886. 1 1642 1.000 3 643 . 2364 4000. ,000 16078. 0. 5179. .322 1166 9 4 485 1854. 552 . 1 165 3447 
20000. .600 5546. 0, 4168. .752 1573 9 5 497 1822 . 516 . I 543 3447 . 4 965. 1 1642 1.000 3 447 . 3350 
869. 1 1642 1.000 3 599. 2483 4000, .000 13797, 0. 4537 , ,329 1082 6 4 486 1791. 548, 1 141 3447 
20000. ,600 4532. 0. 3708 . .818 1517 7 5 670 1765 . 512. 1 504 3447 . 4 949, 1 1642 1.000 3 409. 3610 
854 . 1 1642 1.000 4 555 . 2 62 6 4000 . .000 11661. 0 , 3 959 . .339 996 9 4 453 1728. 545. 1 118 3447 
20000. .600 3623. 0 . 3286. ,907 1464 0 5 855 1708. 508 . 1 469 3447 . 4 934 . 1 1642 1.000 4 374 . 3899 
839. 1 1642 1.000 4 5T4 . 27735 
4 
4000. 
921. 1 
.000 9643. 
1642 1.000 
0. 
3 
3417. 
337 . 
.354 
4268 
907 8 4 43 6 1665. 541 . 1 097 3447 
DATA AT MACH .60, 15000 . FT 
ALTITUDE MACH FN BSHP HF SFC R FLOW BPR BOT T19 PR19 A19 # DATA AT MACH .00. 0 . FT 
T9 PR 9 A9 RR NIT V9 AEXIT ALTITUDE MACH FN BSHP WF SFC R FLOW BPR BOT T19 PR19 A19 
15000. , 600 27327 . 0. 16739. .613 2174 8 3 844 2645. 592 , 2 034 3447 . 4 T9 PR 9 A9 RR NIT V9 AEXIT 
1177 . 1 1642 1.000 2 1349 . 1666 0. .000 54281. 0. 18925. .349 1954 5 4 051 2649. 628. 1 «92 3447 
15000. .600 24805. 0. 15109. . 609 2121 6 3 992 2563 . 586. 1 990 3447 . 4 1233 . 1 1642 1.000 10 977 . 1959 
1142 . 1 1642 1.000 9 1256 . 1693 0. .000 49747, 0. 16997. .342 1876. 6 4 140 2568 . 621. 1 . 452 3447 
15:07:49 B747-FLOPS-OUT 
• 1205 . 1 1642 1.000 ; 306. ; -* 4901€,9 14921.4 10940.7 3 7 71 ? 0 JlCfS i 316JO.J! 2B714.7 25990.4 .iii1.» 2D97-6 .5 
0 000 45120. 0. 15172. .236 17°1 .6 22 2 24 98 615 . 1 410 3447. + 18525.0 16077.8 1JTJ6.7 11661.4 9643.5 .0 
+ 1177 . 1 1642 1.O0C 2 83B. 2144 1&776.6 15062.1 13469.0 12258.8 11137.6 100B9.8 9109.8 B20B.S 7377.1 6612.2 
0 000 41566. 0. 13816. .3^2 1722 8 4 283 2423 . 111 . 1 377 3447 . 5877.7 5178.9 4537.0 3 ^8 8 3416.9 1342.1 
+ 1156. 1 1042 1.000 3 785 . 2215 .342 .335 ,32i .325 .321 .318 .317 .AN .315 • 5 
0 000 38 164. 0 . 12554. .3S9 1653 7 4 338 2359. 606 . 1 3.46 3447 . + .317 .322 .329 .339 .354 .000 
+ 1135 . 1 1642 1.00D 3 73-9 . 2336 
0 000 34734. 0. 11370. .327 1581 3 4 384 2294 . 601 . 1 31S 3147. MACH -- .000, ALTITUDE-: =• 0,, THRUSTS/FUEL FLOWS/SFCS/NOX RAT.i.S FOLLOW 
+ 1115 . 1 1642 1.000 2 637 . 2448 54280.7 49747.0 45120.1 41S65.9 3,611 4.1 34,84.5 31556.0 28538.2 25713,0 22983.O 
0 OOO 31556. B . 10274. .226 1508 4 4 £ ?. i: 2230. 597 . 1 284 3447 . + 20153.2 17412.5 14919.8 12480.3 1034D.3 .0 
+ LOST. ' 1643 1.000 2 6*2, 2571 38925.3 16997.2 15171.9 13315.7 12554.2 11369. FL •11274.3 9262.8 ,1332.S 7165.3 
0 000 28518. 9261. .325 113 6 7 4 449 216S. 593 . 1 25u 3147 . + 6617.3 5819.4 5109.3 4438.4 3^45.u j.514.0 
1077 . 1 1642 1.OD0 2 600 . 2705 .34 9 .3 42 .336 .3 32 .329 .327 .326 .325 .324 .325 
0 000 257i". 0. S3 33 . .r-2 4 13S6 1 4 466 2101. 1 23C 3447 . .338 334 .342 .356 .372 .000 
1057 . 1 1642 1.300 3 . 9. 2851 
0 000 S29B3. 0 . 74 S5 . .325 1293 5 4 477 2 • <" 585 . 1 205 3447 . 8 RSVJ-..7.0 PROPULSION SYSTEM DATA 
1033, 1 1S42 1.000 2 520. 3015 BASELINE ENGICE THRUST THRSO 54ZB0.7 LHF 
0 OOO 20153. 0. 661B . . 32! 1213 0 4 483 1972 . 5B1 . 1 179 3447 . HA.SRMNF F.NGI1TE WEIGHT KKNC 3623.7 LDF 
1021 . 1 1642 1,MOO 4 4 3. 3216 DA.SELINL INLET WEIGHT HTNL 50JO. 7 LBF 
0 000 17413. 0 . 5819 . .3:34 1129 1 4 495 IS 07 . 577 . 1 154 3447 . BASELINE NOZZLE WVKJUT WNOZ 970,6 LBF 
1D05 . 1 1642 1.000 4 440 . 3459 BASELINE NACELLE LENGTH HfAC 17.44 PT 
0 OOO 14920. 0, 5110. .3,2 1046 8 4 470 1. • ' 3 . 573 . Z 131 3447 . BASELINE NACELLE DIAMETER BRAC 7.74 FT 
+ 989 . 1 154 2 1.000 3 404. 371E 
0 OOO 12480. 0 . 443 6 . .356 958 8 4 453 1773. 569 . 1 109 3447 . 
975. 1 1642 1.000 4 3 67 . 4 16 
0 000 10340. 0 . 3845 . .372 874 2 4 410 1714 . 566 . 1 089 3447 . * NAM EL IJ 1 SKISSJiK 
+ 960 . 1 1642 1.000 5 332 . 4409 PERFORMANCE CONTROLS AND FACTORS AND MISSION SEC KENT DEFINJT ! ON 
; "A I.PVEL STATIC MAXIMUM T : UKT 542 F.0, 7 :,B 
GENESAItD PHOPULSTON SV.^TEM WT 
(NEW BASELINE ENGINE THHUST -
ALL POINT ENGINE DEC* SUMMARY 
1787:: 7 Ll 
OVERRULES THkSOl 
LI OW MACH = .950, ALTITUDE - 39000., THRUSTS / •" , FLOWS'SFC S/NOX RATIC 
10498 0 3. 3.6 8579.0 7928.8 7252.3 65B7.fi 5945.7 5307.6 4 6 ii ^ . 1 112.7.9 
3539.7 3081,2 2590.3 2126,8 1682.0 .0 
6803.1 ol54.6 5549.6 5142.0 4742.7 4361.0 3998.6 3651.6 3324.5 3020.7 
2738.2 2472.4 7221.5 19B3.7 1763.9 932.5 
.648 .647 .647 .549 .654 .662 .673 .68B .708 .732 
.761 .802 .358 .933 1.049 .000 
MACH = .f ., ALTITUDE = 35O00., THKU3T3/FUEL FLOWS/SFCS/NOX PAJ'J, ! 1'OLLOW 
12724.8 11526.7 10398.8 9611.4 8791.7 7936.2 7207.9 6434.7 5A91.7 5003.6 
4361!.9 3731.'! 513V,1 2574.9 0 1 5 . 9 . U 
B296.2 7504.8 6706.1 T26A.4 5782.4 5316.7 1P74.5 4451.4 4052.3 3681,6 
3336.8 JOLZ.S 2706.0 >.416.0 2148.0 1135.8 
,651 .63 1 .652 .653 .666 .676 .692 .712 .736 
.765 -807 .6C 3 ."18 1.055 .000 
MACH = .500, ALTITUDE T 20000., THSUSTS/FUEl, FL0W5/SFCE7N0X RATIOS FOLLOW 
23191 1 2U149.1 1*262.9 16776.4 15341.3 13930,9 12512.0 11167.7 9921.6 8716.6 
7569,7 6529.6 1545.B 4532.4 3622 . 8 .0 
13280.3 11990.9 10798.1 3947.8 9141.7 8376.:'• 7640.9 6952.1 6313.5 5714.1 
5156.0 4613.9 4168.5 3707.8 3285.1.- 1603.8 
,598 .595 .551 .593 .596 .601 .611 .623 .636 .656 
. 63 J .711 .7 52 .SIV .907 .000 
MACH - .600, ALTITUDE - 150OO., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
27326.9 24804.5 22477.5 20646.2 13878.6 17145.0 15408.9 13761.3 12232.4 10757.4 
9345.9 8055.5 685S.6 56U3.7 4478.0 .0 
2;TY>. 2 3-108.7 L3C01.8 1<52J.9 U 5 I ? . ? 1054LJ.3 9625.5 B7S9.4 7956.1 7202.6 
6499.6 5354.2 S3 55,2 4673.3 414D.D 2018.7 
-613 .603 .605 .607 .610 .615 .625 .637 .650 .670 
,695 .726 .766 .834 .925 .000 
DESCPT PTT^JFL NAfiF. VALUE DIMEN 
kMJUHANCE MISSION GWITCH INDR 0 
OVERALL FUEL FLOW FACTOR FACT 1 .OOQO 
CDO FACTOR FCDO 1 .0000 
CDI FACTOR f : I 1 .0000 
SUBSONIC CD FACTOR FCDSUB .oooo 
SUP?:KS0NIC CD FSCTOR FCDSU? 1 .0000 
ENGINE SCALING SWITCH 1 
OWE FACTOR OWFACT 1 . uooo 
PRINT FLAG IFIAG 2 
DETAILED MISSION PRINT M3DKPT 0 
TEMPERATURE DEVIATION DTC .0 DEG C 
CALC RAMP WT OR RANGE IRW 1 
RANGE TOLERANCE RTOL . 0C1C N MI 
ATA TFAFFIC ALLOWANCE LATA F> 
WEIGHT :1JCRKME2NT DWT 1. LBF 
GROUND OPERATIONS AND TAKEOFF INPUT 
TAKEOFF TIME 
TAX j -OUT TIME 
APPROACH TIMS 
APPROACH FUEL FLOW 
TA>;-IN TIME 
TAKEOFF FUEL. PLOW 
TAXI FUEL FLOW 
TAKOT:: 
TAXI 'M 
APPRTM 
APPFFF 
PAJflTM 
TAKOi-'F 
TV.PUFL 
HAL!. DE = 4 000. THRUSTS/LI: I'LOWS/SFCS/NOX RATIOS FOLLOW 
INPUT FOR 1 CLIMB SCHEDULES 
MINIMUM CLIMB HACH NUMBER C1J4KJN 
MAXIMUM CLIMB MACH NUMBER CLMMAX 
MINIMUM CL1MR ALTITUDE CLAN IN 
FT 
MAXIMUM CL.MB ALTITUDE CLAMAX 
FT 
NUMBER OF CLIMB STEPS NIMCL 
CLIMB OPTIMIZATION FACTOR PUP 
FOLLOWING CRIUSE SSUHEMT NCRCL 
DKA3 C: liFFIC 7EMT IHCREHIi-JT RI.uCr 
2 . 0 
10.0 
.0 
2,00 
.0 
. 0 
.0 
(1) 
. JODO 
.0000 
0. 
31 
1 .0000 
1 
. ooooo 
VILLI 
MIN 
MIN 
UN 
I.^M/h'R/ENGINE 
l.HM/HR/ENGINE 
1.2) 
.3000 
. 0000 
0. 
• . 0010 
I 
.00000 
(31 
. 3 000 
.0000 
0. 
ni 
.DOIO 
. 3000 
.0000 
0. 
31 
-.0010 
1 
. 000 
Nov 18% 
B747-FLOPS-OUT 
NO. OF POWER SETTINGS IPPCL 1 1 1 1 HOLD CRUISE SCHEDULE NCRHOL 3 
STORE DRAG DURING CLIMB ISTCL 0 0 0 0 HOLD POSITION SWITCH IHOPOS 1 
MAX CLIMB POWER SETTING MAXCL 1 CRUISE ONLY SWITCH ICRON 0 
FAA CLIMB ENFORCED IFAACL 1 2ND RES HOLD TIME OR FRAC THOLD .000 MIN 
FAA DESCENT ENFORCED IFAADE 1 THOLD CRUISE SCHEDULE NCRTH 1 
MINIMUM CLIMB RATE SWITCH NODIVE 0 
MINIMUM CLIMB RATE DIVLIM 0 . FT/MIN 
Q LIMIT IN CLIMB CLIM .0 PSF 
MAXIMUM RATE OF DESCENT RDLIM -99999.0 FT/MIN (t MISSION SEQUENCE DEFINITION 
INPUT FOR 3 CRUISE SCHEDULES (1) (21 13) (41 START MACH NUMBER = ,5170 ALTITUDE = 1500. FT 
(5) (6) CLIMB USE CLIMB SCHEDULE 1 
CRUISE OPTION SWITCH IOC 0 3 4 1 CRUISE USE CRUISE SCHEDULE 1 END CRUISE DISTANCE . 0 N Ml 
+ 1 1 DESCENT 
CRUISE OPT FUEL FACTOR FFUEL i.ooo 1 .000 1 . 000 i.ooo END MACH NUMBER = .3000 ALTITUDE = 0. FT 
+ 1.000 1.000 
CRUISE OPT NOX FACTOR FNOX .000 . 000 .000 .000 
+ .000 .000 
MAXIMUM MACH NUMBER CRMACH .8500 .8500 .7000 .0000 ft USER-DEFINED AERODYNAMIC DATA 
+ .0000 .OOOO 
MAXIMUM ALTITUDE CRALT 40000. 30000, 1500. -1. DRAG DUE TO LIFT 
+ -1. -1. FT 
DRAG COEFFICIENT INCREMENT CRDCD .00000 .00000 .00000 .ooooo MACH/CL ,000 .100 .130 .200 .300 .400 . 4 40 . 500 . 600 
t .00000 .00000 + .700 .300 
STORE DRAG DURING CRUISE ISTCR 0 0 0 0 .300 ,01930 .01810 01800 01840 .02020 .02300 .02480 ,02780 .0343C 
t 0 0 + .04320 .05520 
LONG RANGE CRUISE FACTOR FLRCR 1.000 1.000 1.000 1 .000 .500 .01750 .01630 01620 O1660 .01340 . 02120 .02320 .02660 .03330 
1.000 1.000 •+ .04200 .05420 
MINIMUM MACH NUMBER CRMMIN .5000 .5000 .2500 .0000 .700 .01720 .01600 01590 01630 .01810 .02090 .02260 .02550 .03330 
+ .0000 .0000 + .04520 06100 
MAXIMUM LIFT COEFFICIENT CRCLMX .8000 . 8000 1.0000 .oooo .800 .01780 .01640 01630 01670 .01850 ,02120 .02310 ,02620 .03440 
+ .0000 .0000 .04870 .06470 
ENGINE FEATHERING ALLOWED IFEATH 0 0 0 0 .840 ,0130C .01650 01640 01690 .01870 ,02140 .02320 .02680 .03450 
+• 0 0 + ,05180 .07260 
ENGINE FRACTION REMAINING FEATHF .5000 .5000 .5000 . 5000 .860 .01840 .01680 01670 01720 .01900 .02180 .02350 .02730 .03690 
+ .5000 .5000 + .05570 .07630 
CD INCREASE FOR FEATHERING CDFETH .00000 .00000 .00000 .ooooo .880 .01940 •O1810 01800 01840 .02020 .02300 .02540 .02950 .04160 
+ .00000 .00000 + . 06400 ,08980 
MINIMUM CRUISE ALTITUDE HPMIN looo. 1000 . 1000. 1000. , 900 .02100 .01970 01960 02000 .02210 .02580 .02890 .03400 . 04930 
1000. 1000. FT + .0767C .10830 
INCREMENT IN CRUISE WT, DCWT 1.0 LBF 
RATE OF CLIMB CEILING RCIN 300. 0 FT/MIN LIFT INDEPENDENT DRAG INCLUDING WAVE DRAG, IF ANY 
INPUT FOR DESCENT SCHEDULE ALT/MACH ,300 . 500 .700 .800 .840 . 860 .880 .900 
DESCENT OPTION SWITCH IVS 1 0. -.00170 -.00160 - 00140 - 00140 -.00140 - .00140 -.00130 - .00130 
DESCENT LIFT COEFF. DECL ,8000 5000. -.00150 -.00130 - 00120 - 00120 -.00120 - .00120 -.00120 - .00110 
MINIMUM DESCENT MACH NO. DEMMIN .3000 10000. -.00120 -.00110 - O01OO - 00100 -.00100 - .00100 -.00090 - .00090 
MAXIMUM DESCENT MACH NO. DEMMAX .0000 15000. -.00100 -.00080 - 00080 - 00080 -.00080 - .0007C -.00070 - .00070 
MINIMUM DESCENT ALTITUDE DEAMIN 0. FT 20000. -.00070 -.00060 - 00050 - 00050 -.00050 - .00050 -.00050 - .00050 
MAXIMUM DESCENT ALTITUDE DEAMAX 0. FT 25000. -.00030 -.00030 - 00030 - 00030 -.00030 - .00030 -.00030 - .00030 
NUMBER OF DESCENT STEPS NINDE 31 30000. .00000 .00000 ooooo ooooc .ooooo .00000 ,00000 .00000 
DRAG COEFFICIENT INCREMENT DEDCD .00380 35000. ,ooo4o .00030 00030 00030 .00030 .00030 .00030 .00030 
STORE DRAG DURING DESCENT ISTDE 0 40000. .00090 .00080 00070 OOO70 .00070 .00070 .00070 .OO070 
45000, .00140 .00130 00120 00110 .ooiio .00110 .ooiio .00110 
RESERVE SEGMENT INPUT 
RESERVE CALC. OR CONST IRS 
RESERVE FUEL RESRFU 
FRACTION OF TRIP FUEL RESTRP 
MISSED APPROACH TIME TIMMAP 
RANGE TO ALTERNATE AIRPORT ALTRAN 
RESERVE CLIMB SCHEDULE NCLRES 
RESERVE CRUISE SCHEDULE NCRRES 
START RESERVE MACH NUMBER SREMCH 
END RESERVE MACH NUMBER EREMCH 
START RESERVE ALTITUDE SRJEALT 
END RESERVE ALTITUDE EREALT 
RESERVE HOLDING TIME HOLDTM 
, 000 LBM 
.050 
2.0 MIN 
200.0 N MI 
1 2 
.3000 
.3000 
0 . FT 
1500. FT 
30.0 MIN 
#TITLE, BEGIN OUTPUT OF RESULTS 
B747-400 (PW4056) REV 2.0 
FINAL ANALYSIS 
It CRUISE OPTIMIZATION RESULTS 
SUMMARY DATA FOR CRUISE SCHEDULE 1 
B747-FLOPS-OUT 
WEIGHT 
RATE OF 
CLIMB 
ALTITUDE THRUST FUEL 
CL L/D ENGINES NOX 
AVAILABLE REQUIRED FLOW 
OPERATING RATE 
MACH VELOCITY SPECIFI 
NUMBER 
SUMMARY DATA FOR CRUISE SCHEDULE 2 
WEIGHT ALTITUDE THRUST 
: RATE OF CL L/D ENGINES NOX 
AVAILABLE REQUIRED 
SFC MACH VELOCITY SPECIFI 
NUMBER 
416000. 39574. 26547. 22055 . 13600. . 6166 .7523 431 5 .0317 4 CLIMB OPERATING RATE 
+ 3 471 .9 .4632 18 86 4 0 .00 
432000. 40000. 28580. 23122. 14435. . 6243 . 7781 446 3 .0309 416000. 30000. 48385. 22028 14480. , 6574 . 6598 388 9 .0268 4 
2 571 .0 .45B8 18 6S 4 0 .00 4 6 2495 .5 ,3836 18 89 4 0 .00 
448000. 40000, 29912, 24047. 15093. .6276 .7888 452 4 .0299 432000. 30000. 48839. 22772 14923. .6553 .6683 393 9 . 0264 4 
B 599 .7 .4630 18 63 4 0 .00 4 0 2407.2 .3883 18 97 4 0 .00 
464000. 40000. 30960. 24964. 15729. . 6301 .7972 457 3 .0290 448000. 30000. 49278, 23516 15365. .6534 . 6765 398 8 .0259 4 
7 593 .4 .4695 18 59 4 0 .00 4 s 2322.1 .3930 19 05 4 0 ,00 
480000. 40000. 35158. 26032. 16857. .6476 .8309 47 6 6 .0282 464000. 30000. 49701. 24261 15809, .6516 . 6844 403 A .0255 
+ 7 917.6 .4471 18 44 4 0 ,00 + 2 2240.0 .3977 IS 13 4 0 .00 
496000. 40000, 36027. 26916. 17492. .6499 .8379 480 6 , 0274 480000. 30000. 50219. 25065 16306. .6505 . 6941 409 1 .0250 4 
7 894,0 .4543 18 43 4 0 .00 4 9 2171.2 .4000 19 15 4 0 .00 
512000. 39900. 36466. 27810. 18051. . 6491 . B396 481 6 .0266 496000. 30000. 50B33. 25927 16856. . 6501 .7056 415 9 . 0246 4 
8 824 .5 .4648 18 41 4 0 .00 4 7 2114.8 . 4000 19 13 4 0 .00 
528000. 39402. 37634. 28649. 18609. . 6495 . 8403 482 0 .0259 512000. 30000. 51437, 26790 17411. . 6499 .7169 422 5 .0242 4 
0 830 .7 . 4672 18 43 4 0 .00 4 7 2059.9 ,4000 19 11 4 0 .00 
544000, 38737. 39079. 29445. 19149. .6503 .8403 482 0 .0251 528000. 30000. 52246. 27788 17934. . 6454 .7320 431 5 .0240 4 
7 864 .4 .4 663 18 48 4 0 .00 4 6 2023.9 .3956 19 00 4 0 .00 
560000. 38274. 40095. 30285. 19678. . 6498 .8404 482 1 . 0245 544000. 30000. 52226. 28374 18223. . 6422 .7316 431 2 .0236 4 
0 855.2 .4694 18 49 4 0 .00 4 6 1914.7 .4080 19 17 4 0 .00 
576000. 37764. 40787, 31109. 20139. , 6474 ,8366 479 9 .0238 560000. 30000. 52226. 29048 18563. .6390 .7316 431 2 .0232 l 
3 816 .5 . 4754 18 52 4 0 .00 4 3 1807.5 .4200 19 28 4 0 .00 
592000, 37250. 41874. 31934. 20689. .6479 .83 62 479 6 , 0231 576000. 30000. 52225. 29765 18927. .6359 .7316 431 2 .0227 4 
B 815.5 .4772 18 54 4 0 .00 4 8 1702.8 .4321 19 35 4 0 .OC 
608000. 35699. 45641. 32529. 21387. . 6575 .8400 482 8 .0225 592000. 30000. 52225. 30511 19307. . 6328 .7316 431 2 ,0223 4 
7 1054.4 . 4510 18 69 4 0 .00 4 3 1601.7 .4441 19 40 4 0 .00 
624000. 35109. 46924. 33325. 21941. .6584 .8400 484 1 . 0220 608000. 30000. 52295. 31275 19723. . 6306 .7329 432 0 . 0219 4 
6 1068.3 .4500 18 72 4 0 ,00 4 0 3.512 .5 ,4544 19 44 4 0 .00 
640000. 34600. 48031. 34135. 22490, . 6589 . 84O0 485 2 ,0215 624000, 30000. 52814. 32163 20375, . 633 5 ,7426 437 7 ,0214 4 
7 1066.8 .4506 18 75 4 0 .00 4 8 1466,9 .4543 19 40 4 0 . 00 
656000. 34005. 49322. 34935. 23047. .6597 .8400 486 5 .0211 640000. 30000, 53335. 33064 21038 , . 63 63 ,7522 443 5 .0210 4 
1 1080.4 .4491 18 78 4 0 .00 + 8 1422.4 .4540 19 36 4 0 .00 
672000. 33456, 50515. 35738. 23598. .6603 .8400 4 87 7 .0206 656000. 30000. 54042. 34032 21815. .6410 .7655 451 2 . 0206 4 
7 1086 .0 .4484 18 80 4 0 .00 4 B 1393.9 .4494 19 28 4 0 .00 
688000. 32903. 51718. 36537. 24148. .6609 .8400 488 9 .0202 672000. 3 0000. 54594. 34970 22528. .6442 ,7759 457 3 .0203 4 
t 1092.4 . 4 473 18 83 4 0 .00 4 0 1352.4 . 4482 19 22 4 0 .00 
704000. 32361. 52895, 37336. 24696. .6615 .8400 490 0 .0198 688000. 30000. 55189, 35936 23277. . 6477 .7870 463 9 .0199 
^ 4 1096.8 .4464 18 86 4 0 .00 4 3 1314.5 ,4460 19 14 4 0 .00 
720000, 31843. 54043. 38140. 25250. .6620 . 8403 491 4 .0194 704000. 30000, 55209, 36731 23719, .6458 ,7873 464 1 ,0195 
+ 6 1099.0 .4454 18 88 4 0 . 00 4 7 1233 .5 .4559 19 17 4 0 .00 
736000. 31309. 55182. 38929. 25784. ,6623 .8400 492 3 .0190 720000. 30000. 55209. 37534 24159. . 6436 .7873 464 1 ,0192 4 
9 1100.9 . 4446 18 91 4 0 .00 4 1 1153.7 .4663 19 18 4 0 .00 
752000. 30799. 56292. 39725, 26325. , 6627 , 84O0 493 4 .0187 736000. 30000. 55216, 38354 24611. . 6417 .7875 464 2 .0188 4 
4 1100.8 .4437 18 93 4 0 .00 4 6 1076.9 .47 65 19 19 i 0 .00 
768000. 30297. 57382. 40519. 26863. ,6630 .8400 494 5 .0184 752000. 30000. 5S216. 39186 25078. .6400 .7875 464 2 .0185 4 
1 1099.5 .4429 18 95 4 0 ,00 4 1 1002.0 .4869 19 19 4 0 .00 
784000. 2979S. 58528. 41331. 27433. .6637 .8411 496 2 .0180 768000. 30000. 55217. 40033 25554. .6383 .7875 464 2 . 0181 
+ 9 1102.2 .4408 18 97 4 0 .00 4 6 929.4 .4972 19 18 4 0 .00 
800000. 29429. 59367. 42147. 27981. .6639 . 8420 497 5 . 0177 784000. 30000. 55217 . 41010 26102. .6365 .7875 464 2 .0177 4 
B 1084.5 .4415 18 98 4 0 .00 4 8 851.8 . 5076 19 12 4 0 .00 
816000. 2 9009. 60345. 42976. 28558. .6645 . 8436 499 3 .0174 800000. 30000. 58344, 42306 28064. . 6634 .8459 498 6 ,0177 
+ 9 1076.4 . 4402 18 99 4 0 .00 4 7 1012.3 .4488 18 91 4 0 .00 
832000. 28630. 61213. 43801. 29119. .6648 .8448 500 9 ,0172 816000. 30000. 58562. 43274 28710. .6634 . 8500 501 0 . 0174 4 
C 1061.5 .4400 18 99 4 0 .00 4 5 950.6 .4534 18 86 4 0 .00 
848000. 2 82 61 . 62047. 44626. 29675. .6650 .8459 502 3 .0169 832000. 30000, 58562. 44193 29244. . 6617 ,8500 501 0 .0171 4 
3 1045.0 .4400 19 00 4 0 .00 4 3 876 .3 .4623 18 83 4 0 .00 
864000. 27896. 62865. 45450. 30229. . 6651 .8469 503 7 ,0166 84BO00. 30000. 58562. 45162 29816. .6602 .8500 501 0 ,0168 4 
6 1028.1 .4400 19 01 4 0 .00 4 0 801.8 .4712 18 78 4 0 . 00 
880000. 27534. 63668. 46274. 30781. .6652 .8478 505 0 ,0164 864000, 30000, 58562. 46182 30425, .6588 , 8500 501 0 .0164 4 
1 1010.9 . 4400 19 02 4 0 .00 4 7 727.0 
B80000. 
.4801 
30000. 
18 71 
58562. 
4 0 
47253 
.00 
31065. . 6574 .8500 501 0 .0161 
Nov 18% 
15:07:49 B747-FLOPS-OUT 
+3 652.0 .1890 18.62 4.0 . 00 + 2 4026.4 
880000. 
+ 6 3955.5 
. 600C 
1500, 
.5993 
13 .75 
168250. 
18.77 
4.0 
46888. 
4.0 
.00 
29926. 
.00 
.6382 .4304 283.2 
SUMMARY DATA FOR CRUISE SCHEDULE 3 
WEIGHT ALTITUDE 
CL + C RATE OF L/D 
THRUST 
ENGINES 
FUEL SFC MACH VELOCITY SPECIFI CRUISE SCHEDULE RANGE AND TIME SUMMARY 
AVAILABLE REQUIRED FLOW NUMBER RANGE WEIGHT RANGE -1- TIME RANGE -2- TIME RANGE -3- TIME 
CLIMB OPERATING RATE (POUNDS) (N.MI.) (HR) (N.MI.) (HR) (N.MI. | (HR J 
880000. 0 00 0 00 0 OO 
416000. 1500, 178132. 22657. 17136. .7563 .2957 194 6 .0113 872000, 131 8 26 129 7 26 75 8 27 
+ 6 7365 .7 . 600C 18.36 4 0 00 864000. 264 5 52 260 7 52 151 9 54 
432000. 1500. 177718. 23501. 17543. .7465 .3014 198 3 .0113 856000. 398 4 79 393 1 78 228 2 81 
+ 0 7169.6 .6000 18 .38 4 0 00 848000, 533 2 1 06 526 9 1 05 304 . 8 1 09 
448000. 1500. 177312. 24344. 17953, .7375 .3069 202 0 .0112 840000. 669 2 1 33 662 0 1 32 3 81 6 1 36 
4 5 6983.4 .6000 18.40 4 0 00 832000. 806 2 1 60 798 4 1 59 458 7 1 64 
464000. 1500. 176914. 25186. 183 64. .7291 .3123 205 5 .0111 824000, 944 4 1 88 936. 1 1 87 536 1 1 92 
+ 9 6806.3 .6000 18 .42 4 0 00 816000. 1083 7 2 16 1075 0 2 15 613 7 2 21 
480000, 1500. 176522. 26027. 18777. ,7214 .3177 209 0 .0111 808000. 1224 2 2 44 1215 2 2 43 691 6 2 50 
+ 3 6637,5 . 6000 18.44 4 0 00 800000, 1365 8 2 72 1356 7 2 71 769 7 2 78 
496000. 1500 . 176136. 26867. 19192. .7143 .3229 212 5 .0110 792000. 1508 7 3 01 1498 9 3 00 848 1 3 08 
+ 7 6476.4 .6000 18 ,46 4 0 00 784000. 1652 8 3 30 1641 1 3 30 926 8 3 37 
512000. 1500, 175757, 27707. 19609. .7077 .3281 215 9 .0110 776000. 1798 1 3 59 1784 2 3 61 1005 8 3 67 
+ 1 6322.3 . 6000 18 .48 i 0 00 768000. 1944 7 3 89 1928 7 3 92 1085 0 3 96 
528000. 1500. 175384. 28546. 20028. ,7016 .3332 219 3 ,0109 760000. 2092 6 4 19 2074 7 4 23 1164 5 4 27 
+ 5 6174.8 . 600C 18.50 4 0 00 752000. 2241 9 4 49 2222 1 i 55 1244 3 4 57 
544000. 1500. 175016. 29385. 20448. , 6959 .3382 222 6 .0108 744000. 2392 5 4 80 2370 a 4 87 1324 4 4 88 
4 8 6033.4 .6000 18.51 4 0 00 736000, 2544 6 5 11 2521 0 5 20 1404 1 5 19 
560000. 1500. 174654. 30222. 20871. .6906 .3431 225 8 .0108 728000. 2698 0 5 42 2672 6 5 52 1485 4 5 50 
+ 2 5897 . 5 . 6000 18.53 4 0 00 720000. 2853 0 5 73 2825 5 5 85 1566 3 5 81 
576000. 1500 , 174297, 31060. 21296. . 6857 . 3480 229 0 .0107 712000. 3009 4 6 05 2979 9 6 18 1647 5 6 13 
+ 5 5767.0 . 6000 18.54 4 0 00 704000. 3167 4 6 37 3135 7 6 52 1729 0 6 45 
592000. 1500. 173944. 31896. 21723. .6810 .3528 232 2 .0106 696000, 3326 9 6 70 3293 0 6 86 1810 a 6 78 
+ 9 5641.3 , 6000 18.56 4 0 00 688000. 3488 1 7 03 3451 1 7 20 1892 9 7 10 
608000, 1500. 173597. 32733. 22152. . 6768 .3575 235 3 .0106 680000. 3650 9 7 36 3611 a 7 55 1975 3 7 43 
f 2 5520.2 .6000 18 .57 4 0 00 672000. 3815 3 7 7C 3773 5 7 90 2058 0 7 77 
624000. 1500. 173254. 33568. 22583. .6727 .3622 238 4 .0105 664000. 3981 5 8 04 3936 6 8 26 2140 9 R 10 
+ 5 5403.3 .6000 18.59 4 0 00 656000, 4149 5 8 39 4101 3 a 62 2224 1 8 44 
640000. 1500. 172915. 34404 . 23016. .6690 .3668 241 4 .0104 648000. 4319 3 8 73 4267 6 8 99 2307 6 8 79 
9 5290.5 . 6000 18.60 4 0 00 640000. 4490 5 9 09 4435 4 37 2391 4 9 13 
656000. 1500 . 172581. 35239. 23451. . 6655 . 3714 244 4 .0104 632000. 4664 5 9 45 4604 8 9 75 2475 4 9 48 
+ 2 5181.5 ,6000 18.62 4 0 00 624000. 4840 0 9 81 4775 8 10 14 2559 7 9 83 
672000. 1500. 172250. 36074. 23892. . 6623 .3759 247 4 ,0103 616000, 5017 5 10 18 4943 5 10 54 2644 3 10 19 
5 5076.0 . 6000 18 . 63 4 0 00 608000. 5197 a 10 55 5122 9 10 94 2729 2 10 55 
688000. 1500. 171924. 36908. 24345, .6596 ,3803 250 3 .0102 600000. 5378 8 10 92 5299 0 11 35 2814 3 10 91 
+ 8 4973.9 . 6000 18 . 64 4 0 00 592000, 5563 0 11 31 5476 8 11 76 2899 6 11 28 
704000. 1500. 171601, 37742. 24805. .6572 .3847 253 2 .0102 584000. 5749 8 11 70 5656 3 12 18 2985 2 11 65 
1 4874.9 . 6000 18.65 4 0 00 576000. 5939 1 12 09 5837 7 12 60 3071 1 12 02 
720000, 1500. 171282. 38576. 25268. . 6550 .3891 256 0 .0101 568000. 6131 0 12 49 6020 S 13 02 3157 3 12 40 
+ 3 4778,9 . 6000 18.66 4 .0 00 560000. 6325 6 12 90 6205 8 13 45 3243 7 12 78 
736000. 1500 . 170966. 39410. 25729, .6529 .3934 258 9 ,0100 S52000. 6522 9 13 30 6392 5 13 88 3330 4 13 17 
+ 6 4685.7 .6000 18.68 4 0 00 544000. 6722 9 13 72 6580 9 14 32 3417 3 13 56 
752000. 1500. 170654. 40243. 26189. . 6508 .3976 261 7 ,0099 536000, 6925 7 14 14 6771 0 14 76 3504 5 13 95 
+ 9 4595.2 , 6000 18.69 4 .0 00 528000. 7131 4 14 57 6962 7 15 20 3592 0 14 35 
768000. 1500 , 170346. 41077, 26651. .6488 .4018 264 4 .0099 520000. 7340 2 15 00 7155 5 15 65 3679 7 14 75 
4 2 4507.3 .6000 18.70 4 0 00 512000, 7552 0 15 44 7349 3 16 11 3767 6 15 15 
784000. 1500. 170040. 41910. 27114. . 6470 . 406C 267 2 ,0098 504000. 7767 0 15 89 7544 2 16 57 3855 a 15 56 
4 5 4421.8 . 6000 18 .71 i 0 00 496000. 7985 2 16 34 7740 8 17 04 3944 3 15 98 
800000. 1500. 169737. 42743. 27579. . 64 52 .4101 269 9 .0097 488000. 8206 5 16 80 7939 0 17 52 4033 0 16 40 
+ 9 4338.5 .6000 18.72 4 0 00 480000. 8431 1 17 27 8138 a 18 01 4121 9 16 82 
816000. 1500. 169438. 43576. 28044. , 6436 . 4142 272 6 .0097 472000, B653 8 17 76 6340 4 18 50 4211 1 17 25 
2 4257.5 . 6000 18 .73 4 0 00 464000. 8889 7 18 25 8543 7 19 01 4300 5 17 68 
832000. 1500. 169141. 44409, 28512, . 6420 .4182 275 2 .009 6 456000. 9124 0 18 77 8748 7 19 52 4390 2 18 12 
+ 5 4178.5 . 6000 18.73 4 0 00 448000, 9361 9 19 29 8955 4 20 03 4480 1 18 56 
848000. 1500. 168848. 45242, 28980. . 6406 .4222 277 9 .0095 440000. 9603 6 19 83 9163 9 20 56 4570 2 19 01 
9 4101.5 , 6000 18 .74 4 0 00 432000. 9849 0 20 38 9374 2 21 09 4660 5 19 47 
B64000, 1500, 168557. 46075. 29451. , 6392 .4262 280 5 .0095 424000. 10097 9 20 94 9586 3 21 63 4751 0 19 92 
.0094 
15:07:49 B747-FLOPS-OUT 
S15000. 10350.0 21.52 9800.2 Z2. 18 
# RESERVE NUMMARY 
MISSED APPROACH FUEL 
START HOLDING 
RESERVE -vHD 
RESERVE FUEL 
FUEL RESERVE MACH 
WEIGHT 
HEIGHT NUMBER 
0. LB. 
CLIMB CLIMB CRUISE 
DIST FUEL DIST 
ALTITUDE VELOCITY 
416000. 8619. 29.6 5334.8 79.9 
L 95 L?0, 3964=0. . I 8 30000. 388.<j 
132000. 4619. 31.1 5576.1 IL.9 
19713. 4 12237. .6683 30000. 393.9 
44SU00. BH05. 32.8 5=25.- 75.7 
20D92. 437906. .6765 30O00. 398.8 
464DD0. 9005. 34.5 6080.0 73.9 
20487. 443513. .6844 30000. 403.4 
4800CO. 9106. 36.3 6346.1 71.8 
20891. 459309. .6941 30000. 409.1 43'.:000.
 9409. 38.2 6624.8 69.5 
21292. 474708, .7056 3O000. 415.9 
512000. 9012. 4D.2 6915.9 66.9 
2H98, VJU302. .7169 30000. 422.5j 
&2B0C0. 18.17. 42.5 7226.1 64.1 
22091!. 505902. 7320 30000. 431.5 544000.
 .10023. 44.4 7523.2 61.3 
22495. 521505 .7216 30000. 431.2 
560000. 102JO. 46 1 7797.7 58.9 
22914. 137066:. .7316 JUO'JO . 431.2 
576000. 1043H. 47.9 8079,3 56.8 
23351. 552649. .7376 30000. 431.2 
592D00. 10647. 4.-I.7 8368.7 54.8 
23797. 56ft2!73. .7316 3O000 . 431.2 
60BOOO. 10857. 51.6 8667.6 52.7 
24252. 58374*. .7329 300O0. 432.0 
624000. 11068. =3.8 8992.4 50.2 
24 /17. 599233. . 742', 30000. 437.7 
640000. 1I2U0. '36.2 J351.9 47.2 
25193. 634807. .7523 30(00. 443.5 
656000. 11493. 58.8 9730.0 43.9 2566H.
 610332". .7655 30000. 451.2 
672000. 11707. 61.6 10127.4 40.3 
26145, 645852. .7759 30000. 457.3 
6BBOO0. 11922. L4.4 10531.1 3 6.6 
26629. E6J371. .7870 3O0OO. 463,9 
71)4000. 12140. 67.2 10930.7 33,2 
27115. 476385. .76*73 30000. 464.1 
720000. 1236^. 69.6 11298.6 30.5 
27406, 692194. .7873 30000. 464.1 
7JSQO0. I2SS6. .2.1 11678.7 28.3 
23126. 707P-74. .7875 30DOD . 464.2 
752UO0. 12PC9 74.7 12D73.3 25.9 
2864.1. ?233r-9. .7875 3 0000. 464.2 
76*000. 13032. 77.4 12479.8 23.3 
23TJ2. 738848. .7875 lOOOt- 464.2 
7A4000. Ii254. 80.3 12902.3 20.6 
29466. 75417-4, .Vd75 30OO0. 464.2 
800000. 134S0. 83.:. 13379.4 17.3 
302L2. 7697SB. .3459 .30000. 498.6 
816000. 13793. 93.7 14236.3 9.4 
3Q34 5. 7B5155. .8500 ."MJOOO. 501.0 
332000. 13S12 . 94.2 14740. Li 3.1 
CRUISE 
L'UEL 
2986 . 9 
2932 .5 
2893 . 7 
2876 .9 2 83 8 .
 8 
2793 ,3 
2729 . 8 
2651.8 
2563 . I 
2503 .2 
2458 . 3 
::• 
2369 . 1 
13J03 .0 
2208.8 
209D . 6 
1955.7 
1812 . S 
1675 . 7 
1567 . 8 
1479 . 6 
1380.3 
12 64 , 2 
1139 . 6 
974.2 533
 .7 
177 .1 
20.39 
DESCENT 
DIST 
91.0 
91.5 
91.6 
91.9 
92 .3 
92 .9 
93 . 4 
94 . 2 
95.0 
95.3 
95 . 5 
95 . a 
96 . 0 
96. 6 
97 . 3 
98.2 
99 . 0 
99 . 6 
99 . 8 
99 . 6 
99.3 
99.3 
99 .1 
99.2 
99.9 
102 .7 
DESCENT 
FUEL 
2609 . 4 258ri .7 
2562.4 2521
 .O 
2499.9 
2465.4 
2439 . 3 
2402 .9 
2384 .7 
2382.9 
2375.8 
2366 .1 
2358.7 
2354 .2 
2353.0 
2354.8 
2357.7 
2362 . 1 
2368.2 
2377 .4 
23 82 . 1 
2378.3 
2376,I 
23 1-7:1 . 1 
2378.1 
2371.1 
2386.2 
31236. 
849DDO. 
31754. 
364000. 
32294. 
860000, 
3 2!>42 . 
100764. 
K16246. 
14387. 
331706. 
14615. 
847158. 
* ITEHAT!OH 
* ITERATION 
* ITERATION 
* ITERATION 
* ITERATION 
* ITERATION 
* ITERATION 
* ITERATION 
* ITERATION 
. f 
S7 
.85C-
1DO 
.3500 
104 
. 8500 
RANGE = RANGE = 
RANGE H 
RANGE ± 
RANGE = 
RAT • 
RANGE = 
RANGE = 
RANGE = 
30000. 
4 15226. 
30000. 
? 15743. 50,0,00. 
5 162-6. 
30000. 
8226.463 
7602.859 
7304.941 73(12 .734 
7296.458 
7300.080 
7299.967 
7299.991 
7299.999 
7 . C 
a -.2 
501 . 0 
3 -3.5 
501.0 
7 -7.0 
501.0 
-14 
-210 
-424 
» OUTPUT FROM THE WEIGHTS MODULE 
DESCRIPTION 
CALCULATED WIN:: 
CALCULATED ASPS 
.REA 
r RATIO 
WING LENDING FAC 
ENGIE^ INERTIA RELIEF FACfQS 
WING WEIGHT BREAKDOWN 
TERM 1 
TERM 2 
I'M i 
WING SPAN 
WING GLOVE AREA 
HORIZONTAL TAIL AREA WPIFIED volue:
 .•OEFFICISN." 
VERTICAL TA3I. AKEA 
MODIFIED VOLUME COKFFI!' LENT 
NACELLE LENGTH 
NACELLE DIAMETER 
LENGTH OF MAIN UEAR 
LENGTH OF NOSi. 7E/-R 
MAXIMUM LANDING k'ELGHT 
WING .-TEi- CAPACITY 
FUSELAGE FUEL CAPACITY 
AUXILIARY TANK CAPACITY 
TOTAL FU--;:, CAPACITY 
* * * INSUFFICIENT FUEL CAPACITY 
KASS AND BALANCE SUMMARY 
i/:EF HORi CU-INCHES 
FOR GROSS WEIGHT -
FOR GROSS" WEIGHT = 
FOR GROSS WEIGHT -
FOR GROSS WEIGHT = 
FOR GROSS WEIGHT = 
FOR ::KT.vS ".-.!• :G.::T = 
FOR GROSS WEIGHT = 
FOR GROSS WEIGHT = 
FOR GROSS WEIGHT = 
VA : DIMENSIONS 
60Q4.2 SQ FT 
7 . 18254 
10.1508 
. 8743 53 
49402.0 I Li 
27598.7 LB 
14368.1 L3 
207.67 FT 
.00 SO FT 
1470.00 SQ FT 
2.152473 
810.00 SQ FT 
.159254 
17.80 FT 
7.90 FT 
102 .9 
102.7 
102 . 5 
87C0C0.00 
821413. .51 
797817.08 
797425.77 
796940.77 
797214.49 
797208.45 
797210.23 
7,J77i0.91 
141 . 7N 111.70 IN 
318B84.4 LB 
210227.0 LB 
116556.1 
.0 
" (.1 LB 
2132.5 
2374.5 
2364,4 
PERCENT WFUEP ?EhCEN 
; NOV IS % 
15:07:49 B747-FLOPS-OUT 
WING 
.0 
.0 
.0 
.0 
.0 
.0 
.0 
.0) 
. 0 
4.C 
.0 
.0 
.4] 
.0 
.0 . o 
,c 
. 0 
.0 
.0 
.0 
. c 
HORIZONTAL TAIL 
.0 
VERTICAL TAIL 
.0 
VERTICAL FIN 
. 0 
FUSELAGE 
.0 
LANDING GEAR 
.0 
NACELLE (AIR INDUCTION! 
.0 
STRUCTURE TOTAL 
( .0) 
ENGINES 
.0 
THRUST REVERSERS 
106.8 
MISCELLANEOUS SYSTEMS 
.0 
FUEL SYSTEM-TANKS AND PLUMBING 
.0 
PROPULSION TOTAL 
( 11.5) 
SURFACE CONTROLS 
.0 
AUXILIARY POWER 
.0 
INSTRUMENTS 
.0 
HYDRAULICS 
,0 
ELECTRICAL 
.0 
AVIONICS 
.0 
FURNISHINGS AND EQUIPMENT 
. 0 
AIR CONDITIONING 
.0 
ANTI-ICING 
. 0 
SYSTEMS AND EQUIPMENT TOTAL 
0) < .0) 
WEIGHT EMPTY 
1 1.8 
CREW AND BAGGAGE-FLIGHT, 2 
, 0 
-CABIN, 13 
.0 
UNUSABLE FUEL 
. 0 
ENGINE OIL 
.0 
PASSENGER SERVICE 
. 0 
CARGO CONTAINERS 
.0 
. 0 
.0 
.c 
.0 .c 
.0 OPERATING WEIGHT 
.1 1.7 
PASSENGERS, 
11.52 
1.11 
.60 
.12 
9 .91 
2.31 
,91 
I 26.48) 
5. 05 
.68 
. 17 
.39 
I 6.29) 
.75 
.24 
. 13 
. 48 
.69 
.30 
5 .15 
.55 
.05 
[ 8.34) 
41.12 
.06 
.26 
.16 
.05 
1 . 09 
. 44 
43 . 18 
8.53 
91869. 
8851 . 
4799 . 
938 . 
78968. 
18443. 
7225. 
( 211141.) 
40284. 
5390. 
1387 , 
3102 . 
( 50164.) 
5983 . 
1905, 
1055. 
3829. 
5473 . 
2392 . 
41050. 
4402 . 
414 . 
( 66503.) 
327808. 
450 . 
2105. 
12 69 . 
403 , 
8686 . 
3500. 
344220. 
67980. 
+ .0 .0 
PASSENGER BAGGAGE 
+ .0 .0 
CARGO 
t .0 .0 
ZERO FUEL WEIGHT 
t .0 1.3 
MISSION FUEL 
t .0 .0 
RAMP (GROSS) WEIGHT 
+ .0 .7 
t NONCRUISE SEGMENT RESULTS 
CLIMB PROFILE DATA FOR SEGMENT 1 
- - CUMULATIVE - - -
WEIGHT ENERGY ALT MACH 
2 . 27 
.00 
53 . 98 
46. 02 
100.00 
18128 . 
0. 
430328 . 
366383. 
797211. 
- - INCREMENTAL- -
TIME DIST FUEL 
TIME DIST FUEL CL L/D THRUST /TMAX 
797211 6624, 1500 517 340.2 5970. 1 ,00 0 0 375 0 
.00 0 .0 376 19.93 173132 1.000 
796963 7411. 4286 408 265.7 4339 . 1 .15 6 247 9 210 5 
.15 6 247.9 670 17.69 173565 1 .000 
796420 8971. 5714 418 271 .2 4175 . 1 .37 1 6 543 4 210 0 
.52 2 2 791.3 671 17.65 166168 1 .000 
795873 10538. 7143 429 276 . 9 4004 . 1 ,38 1 7 546 9 209 5 
.90 4 0 1338.2 672 17 .62 158809 1,000 
795321 12110. 8571 441 282 .7 3825. 1 .40 1 9 551 5 209 0 
1.30 5 8 1889.7 673 17 . 58 151491 1.000 
794764 13690. 10000 452 2 88 .7 3639 , 1 .42 2 0 557 5 208 4 
1.73 7 8 2447.2 675 17 .54 144216 1.000 
794255 15224. 10000 538 343 .5 4344 . 1 .38 2 0 508 6 295 1 
2.11 9 9 2955.8 476 19.92 139048 1 .000 
793787 16759. 10000 612 390.7 4666. 1 .34 2 1 468 5 381 8 
2.45 11 9 3424.3 3 68 19 .57 134152 1.000 
793331 18294. 1000C 673 432.8 4566. 1 .33 2 3 4 55 9 4 68 5 
2 .7B 14 2 3880.2 300 17 . 59 127752 1.000 
792875 19828. 10901 706 449.1 4323. 1 .35 2 5 455 9 490 2 
3.13 16 8 433 6.0 286 17 .02 121946 l.OOC 
792413 21363. 12362 713 450.9 4070. 1 .37 2 7 461 9 471 8 
3 .50 19 5 4797.9 297 17 .32 116371 1 , 000 
791945 22898. 13995 713 448.5 3816 . 1 ,39 2 9 467 7 442 8 
3 .88 22 4 5265.7 317 17 . 90 110790 1.000 
791471 24433. 15470 720 450. 0 3569 . 1 . 42 3 1 474 6 424 9 
4.30 25 5 5740.2 330 18 . 22 105435 
1. ooo 790987 25967. 16961 725 451 .0 3321. 1 .45 3 3 483 3 406 5 4 .75 28 8 6223.5 344 18.53 100197 1 .000 
790494 27502. 18453 731 452 .1 3074 . 1 ,48 3 6 493 9 388 7 
5.23 32 4 6717.5 360 18.81 95092 1.000 
789987 29037. 19952 737 4S3 .0 2828. 1 .52 3 9 506 9 371 0 
5.75 36 4 7224.3 377 19 .08 90110 1 .000 
789464 30571. 21480 742 453 .2 2584 . 1 .57 4 3 522 4 352 5 
6 .31 40 6 7746.7 396 19.39 85179 1 ,000 
788925 32106. 22713 758 460 . 6 2398 . 1 , 62 4 7 539 6 349 C 
6.93 45 3 8286.3 400 19 .36 81315 1.000 
788367 33641. 23870 777 469 .8 2238 . 1 . 66 5 1 557 7 348 8 
7 .59 50 4 8843.9 400 19 .26 78015 1.000 
787789 35175. 25012 796 479.1 2093 . 1 .71 5 6 577 5 348 5 
8 .30 56 0 9421.5 400 19.15 75105 1.000 
787189 36710. 26193 814 4 87 .4 1948 . 1 .76 6 1 600 4 345 9 
9 .06 62 2 10021.9 403 19.05 72393 1.000 
NovJKn 
15:07:49 B747-FLOPS-OUT 
786561. 38245. 27436. ,829 494.1 1803, 1 
t 9.88 68.9 10649.5 .409 18.98 69774. 1.000 
785897. 39780. 28873. .838 496.3 1616. 1 
+ 10.78 76.3 11313.5 .427 18,99 66653. 1.000 
785490. 40666. 29761. .841 496.3 1490. 1 
+ 11.35 81.0 11720.6 .441 18.97 64692. 1.000 
DESCENT PROFILE DATA FOR SEGMENT 
- - - CUMULATIVE - - -
WEIGHT ENERGY ALT MACH VEL 
TIME DIST FUEL CL L/D THRUST 
11 
15 
19 
28 
32 36 
40 ,8 
45 
466992 
.00 
467323 
-2.03 
46751C 
-3.20 
467687 
-4.36 
467856 
-5.49 
468015. 
-6.61 24 
468166. 
-7.70 
468308 
-8.78 
468438 
-9 .80 
468560 
10.80 
468673 
11.78 
468779 
12 .74 
468878 
13.66 
468971 
14 .52 
469061 
15.36 
469150 
16 . 17 
469237 
16.97 
469322 
17 .75 
469405 
18.50 
469479 
19 . 19 
469537 
19.79 
469584 
20.34 
469628 
20 .89 
469670. 
21.42 98 
469709. 
21.95 102 
469747. 
22.47 105 
469783, 
0 
0 
2272 
3 
3739 
9 
5208 
2 
667a 
6 
B150 2 
9622 
1 
11097 
49 
53 
57 
61 .8 
56 
70 
74 
78 
82.8 
86 .8 
90 
94 
1743 , 
.0 
4309 . 
,0 -331 
5857 , 
.2 -517 
7411 . 
.4 -695 
8971. 
.7 -863 
10538, 
.0 -1023 
12110. 
.2 -1174 
13690 
.S -1316.4 
15224. 12528 
.7 -1446.3 
16759. 13955 
1567.9 
18294. 15379 
.0 -1681.4 
19828. 16782 
.1 -1787.2 
21363. 17792 
,3 -1885.8 
22898. 18880 
.5 -1978.9 
24433. 20218 
2069.2 
25967. 21559 
.0 -2157.8 
27502. 22894 
.2 -2244.8 
29037. 24224 
.4 -2330.2 
30571. 25279 
.7 -2413.2 
32106. 25704 
2487.4 
33641. 26244 
-2544.8 
35175. 27504 
6 -2591.8 
36710. 28749 
4 -2636.0 
38245. 30002 
2 -2677.7 
39780. 31262 
0 -2717.1 
41314. 32509 
8 -2754.7 
42849. 33768 
.300 198 
.620 16.32 
.327 214 
.568 16.68 
.335 218 
.571 16,65 
.343 223 
.574 16.62 
.352 227 
.577 16.59 
.361 232 
,580 16.56 
.371 237 
.583 16,54 
.381 242 
.586 16.51 
.390 246 
. 590 16.48 
.400 251 
.594 16.45 
.410 256 
.598 16.41 
.422 262 
.600 16.39 
.458 284 
.529 16.67 
.488 301 
,488 16.77 
.503 308 
487 16.78 
.517 315 
.487 16.78 
.531 322 
488 16.78 
.546 325 
.490 16.78 
.575 345 
462 16.78 
.633 380 
3S3 16.17 
.683 408 
342 15.08 
.699 416 
345 15.09 
.716 424. 
348 15.08 
.732 431. 
352 15.10 
.748 438. 
357 15.14 
.765 446. 
362 15.16 
.781 452. 
0. 
5 -
0 . 
6 -
0. 
6 -
0 . 
7 -
0. B -
.3 
1 -
RCI PC 
/TMAX 
1231. 0 
.000 
1303. 0 
.000 
1330. 0 
.000 
1359, 0 
.000 
1389. 0 
.000 
1420. 0 
.000 
1452. 0 
.000 
1484. 0 
,000 
1516. C 
,000 
1550. 0 
.000 
1584. 0 
.000 
1620, 0 
.000 
1725. 0 
.000 
1820. 0 
.000 
1862. 0 
.000 
1904. 0 
.000 
1947. 0 
, 000 
1990. 0 
.000 
2087. 0 
.000 
2381. 0 
.000 
2745. 0 
.000 
2794. 0 
.000 
2847. 0 
.000 
2894. 0 
.000 
2935. 0 
. 000 
2978. 0 
,000 
3014. 0 
.82 6.7 627.6 340.0 
.90 7.4 664.0 325.7 
.57 4.7 407.1 315.3 
- - INCREMENTAL- -
TIME DIST FUEL Q 
,00 
-2.03 
-1.18 
-1.16 
-1 .14 
-1,12 
-1.10 
-1.08 
-1.02 
-1. 00 
-.98 
-.96 
-.92 
-.87 
-.83 
- . 82 
- .80 
-.78 
- .75 
-.69 
- .60 
- .55 
- .54 
-.53 
-.53 
- . 52 
- .51 
.0 
7,0 
4.2 
4 .2 
4.3 
4.3 
4.3 
4.3 
4.2 
4,2 
4 . 1 
4 . 1 
4.2 
4.2 
4.2 
4 . 2 
4.2 
4,2 
4.2 
4 . 2 
3.9 
3 . 8 
3.8 
3.8 
3 .8 
3 . 8 
3.8 
.0 
-331.3 
-186.5 
-177 .4 
-168,4 
-159.5 
-150.9 
-142.4 
-129 . 8 
-121.6 
-113.6 
-105.8 
-98.6 
-93 .2 
-90.3 
-88. 6 
-87 . 0 
-85.4 
-83 . 0 
-74 .1 
-57.5 
-47.0 
-44.2 
-41.7 
-39.5 
-37.6 
-36.0 
133.3 
145.7 
145 . 0 
144 .3 
143 . 6 
142.9 
142.2 
141,4 
140.6 
139. 6 
138.6 
138 ,3 
156.8 
170.1 
170.6 
170.4 
170,1 
169 .7 
179 . 8 
214 .2 
242.8 
240.7 
238.8 
236 .2 
233 .0 
229.9 
226 .1 
+ 22.98 109.7 -2790.7 .368 15.22 0. .000 
469820. 44384. 35172. .792 456.2 -2987. 0 -.51 
* 23.49 113.5 -2827.7 .383 15.46 0. .000 
469859, 45918. 36666. .797 457.2 -2928. 0 -.52 
+ 24.01 117.5 -2866.7 .405 15.81 0. .000 
469897. 47453. 37906. ,810 464.4 -2967. 0 -,52 
+ 24.53 121.5 -2905.0 .417 15.85 0. .000 
469935. 48988. 39439. .810 464,4 -2937. 0 -.52 
+ 25.05 125,5 -2942.6 .449 16.02 0. .000 
469948, 49549, 40000. .810 464.4 -2928. 0 -.19 
*• 25.24 127.0 -2956.4 .461 16.06 0. .000 
3.9 
3.9 
4.0 
4.0 
1 . 5 
-37 ,0 
-39.0 
-38,3 
-37 . 6 
-13 .8 
217.3 -
205.1 -
199.4 -
185.3 -
180.4 -
» ITERATION 10 RANGE = 7300.000 FOR GROSS WEIGHT 797210.95 
It SIZING AND PERFORMANCE RESULTS 
CONFIGURATION DATA AFTER RESIZING (IF ANY) 
OPERATING WEIGHT EMPTY 
PAYLOAD 
MAXIMUM FUEL 
GROSS WEIGHT 
REFERENCE WING AREA 
WING LOADING 
THRUST PER ENGINE 
ENGINE SCALE FACTOR 
THRUST-WEIGHT RATIO 
344219.8 LB 
86108.0 LB 
366883.2 LB 
797211.0 LB 
5651,00 SQ FT 
141.07 LB/SQ FT 
56S70.0 LB 
1 . 0422 
.2838 
MISSION SUMMARY 
+ H NUMBER 
SEGMENT 
+ T END 
TAXI OUT 
TAKE OFF 
+ .517 
CLIMB 
+7 .841 
CRUISE 
<• 1 .810 
DESCENT 
+ 0 
INITIAL FUEL(LB) TIME(MIN) 
ALTITUDE(FT) NOX EMISS(LB) 
WEIGHT(LB) SEGMT TOTAL SEGMT TOTAL 
START END SEGMT TOTAL 
DISTANCE(N Mil 
SEGMT TOTAL 
797211. 
797211. 
1500. 
797211. 11721. 
1500. 29761. 
785490. 315542. 
29761. 40000. 
469948. 2956. 
0, ,300 40000. 
466992 . 
430328. 
RESERVES 
TAXI IN 
ZERO FUEL 
36664. 
0. 
11721. 
.00 
327263. 
, 00 
330219. 
.00 
366883 . 
10.0 
2.0 
11.3 
878 .2 
,00 
25.2 
.00 
.0 
10. 0 
12 .0 
23 .3 
901 . 5 
926.7 
926 ,7 
B1.0 
7092.1 
127 .0 
BI .0 
7173 , 0 
7300.0 
MAC 
STAR 
,51 
.84 
.81 
DESIGN RANGE 
FLIGHT TIME 
7300.0 
914.7 
BLOCK TIME = 15.45 HOURS 
BLOCK FUEL = 330219,0 POUNDS 
TOTAL NITROGEN OXIDES EMISSIONS 
ATA TRAFFIC ALLOWANCE = 
AIR MANEUVER = 46.4 
AIRPORT TRAFFIC ALLOWANCE =17.4 
AIRWAY DISTANCE FACTOR = 146.0 
0. POUNDS 
209.8 NAUTICAL MILES 
ATA RANGE 7300.0 NAUTICAL MILES 
Nov 1896 
15:07:49 B747-FLOPS-OUT 
DOBJ/VAR/CONSTR SUMMARY 
FUEL RANGE VAPP FAROFF FARLDG AMFOR SSFOR GW AR THRUST 
SW TR SWEEP TCA VCMN CB W/S T/W 
366883.2 7300.0 96.9 9206. 4475. 111994. 64987, 797211.0 7.631 56570.0 5 
651.0 .245 37.50 .0800 .850 40000. 141.1 .284 
DESIGN - TIT OPR FPR BPR TTR (SLS) ST VJET (CRUISE) MACH 
ALT THRUST SFC OVEFF CDT CDP 
2572.0 27.700 1.5600 4.0000 1.0300 28.4 988.2 .85 
39000. 10498. .6480 .3176 1358.0 148.62 
VAPP= 
FAROFF= 
FARLDG= 
96.9 
9206. 
4475 . 
Appendix D 
Page 57 
Appendix D. C17 ACSYNT Input & Output File 
Nov 18 96 
C17-SHORT-ACS YNT-IN 
5 D; . . NLEGCR 0, WNT& * 1, * FALSE 
MCDONNELL 7LA.7 C- 17 TRANSPORT MISSION ** SEND 
S DATA BLOCK B 
6 1 .24E+05 
I 0 a 0 
0 c 0 MACH NO. ALTITUDE HORIZONTAL MO. VIND 
S 1 Vi'A BLOCK V 
PHASE SI iSfl END START END DIST TIME TURN •U"S WKFUEL M TP 
:X W B END - - - - -.:,AM5P0RT CLIMB 0- 50 o,oo 0.0 0. :, 0.0 230,0 1 ODOO 1 2 -10 0 
5 3 5 57D F." 1 0 0 2 C, 7 C 
CLIMB o. 
• 0 0.00 -1 28000 0.0 0.0 0.0 310.0 1 tfOOO 2 -1 D 0 a.oooi 
0 . SO BSOOGG.OO 0 . 00 0. 00 0.00 CRUISE 0. I U.75 28000 -1 2000.0 
0 . 3 o.o 0.0 1 oooo 1 4 0 0 9 6 1 2 1 4  0iC 
0 . 00 1000D 0.0 0,0 0.0 2S0.O 1 ^ 1 2 -10 0 : 2 6 CtWB 0. 3 0.00
 -1 
28000 0.0 L . 0.0 1O.M 1 1 2 -too 
0 13 1 
C:U-:SE o. 
75 0.75 2 8000 -1 500. a.o 0.0 0.0
 1 
0000 1 4 ooo 
TRANSPORT *• WCDAC C -17A THAKSFORT AERODYNAMICS MODULE K • 
* • " ' FjCriflC C-17 TRASSPORT SACHAR 
SOFTS ABOSH m 0.220, ALMAX 20 .000, AMC = 3i.O00, 
KGTO =5BD0DD 000, 1C-RAPH = 1, EDNOSE 21.060, BTEF i ooo. RALOIT = Q .000, 
SEND RCLMAX I.OOO, ROC = 0 075, ROCiMJ - .0,70. 
SFIXW : 1.000, SMNDR 0 . 860, HACHN - 0 .750, 
IJCRLW 500 ooo. WCAKGO = 124.000.0 SPAMAC O.uoo, SWPMAX 6(: . 000, SWPM1N 0 .ooo, 
SEND XCDC o.soo, MCDW = 0 . 600, AJCAH - 0, 
> *-** MCDONNELL DOUGl 
IS c -17A TRANSPORT GEOMT.TKY * + * * * ALLLJ 3, INORM 1, ISHPDR • SWING ISUPCR 0, ITHAP • 0, IKCD - 1, AR = 7 200, AREA = 3300,000, DINED 000. ELLIPC =F ELLIM • CLO - 0 . 000, 
L FLA PC 0 110, SHEEP 25 000, TAPER = :"'. 300, o.ooo. 0 .000, 0 .000, 
TCP.OQT 0 135, TCTIP 0 107, TFLAi-C 0 . 170, 0.000, 0 0 .ouo, 
VlttKAC 0 soo. XM7NG 0 290, ZROOT 0 900, o.ooo. 0 ooo. 0 .000, 
KSWEEP 1, CLOC o.ooo. 0 .ooo. o.ooo, •TvEND 0.000, 0 . 000, 0 .000, SHTAIL o.ooo. 0 .000, " .ooo, 
AR 000, AREA 000, CV1 T 1. ooo. 
0.000, 
CLOW 0 000, o .000, 
SHBEJ 27 000, TAPER = 0 400, TCROOT 0 C90, o.ooo. 0 000, 0 .000, 
TCTIP O 080, 
X- ; ML -0 010, ZROOT i. 765. 0.000, 0 .ooo, Q.0O0, J(SHEEP 1, 0.000, 0 .ooo. CMO = D . 000. SEND o.uoo, D .000, 0 . 000, 
5 VTAIL o.ooo, 0 ooo, 0 .000, 
Alt 1 000, AREA 685 000, CWT 0 iop. O.OOD, 0 ooo, 0 ,ooo. 
SHEEP 41 000, SWFACT 1 000, TA5ER 0 . 9*0, SMNSWP o.ooo, 0 .000. 0 .ooo, 
TCRCOT = 0 110, TCTIP 0 110, VTNO . ooo, 0.000, 0 ooo, 0 .000, XV.
 ill = o .37 i , YROOT 0 000, ZKOOT = . 700, ,, ™-1 a ooo, 0 .007. KSV L:EP 1, o.ooo, YSWP ) ooo, 0 .c SEND o.ooo. 0 ooo, 0 .000, Sv:
:
 3 o.ooo. Q .coo. c .ooo, ; 1AM 10 ooo, .JGTK 10 000, X -0 . 750, 0.000, 0 .000, V 0 301 , Z = 0 23 3, SWFACT 1. 0O0, SEND 
SEND SAMUTT 
:•' -7 CSF i.ooo, ESSF 1 ooo. • .) = i .000, 
DIAM 10 000, LENGTH 10 000, X -1, 000, FCEF i.ooo, KM, 1 .000, pew i .ooo, 
Y = 0. 591, Z 0 230, SWFACT = 1. 000, FCDU 1.000, FCDWB 1 .ooo, FENG = i .ooo, 
•v-ENE 
FINTF i.ooo, FLBCOR = 1 
.Oi i, FLO = I . 002, f Kirs 
H Ef-.R i.ooo, FMSR 1 .010, FCDRA - I .ooo. 67DMAX 21 060, l-'JDl 160 >.: .'0, FRAE 3 . 590, l.ooo, 1 ooo. 1 .000, 
FRATIO 
0 000, FRN = 1 000, 1,000, 1 .000, i .000, 
SKNO i.ooo. 1 .000, . 3, 
$ENGINE SEND 
DIAM 3 ooo, N = 4, OUTCOD 3, SATRIM 
SEND CAND o.ooo, CF1AP 10 000, CGM = 0 250, 
5$:5SS$S$SSS$ IT 0,000, SFLAP 700 .000, SM = 1 .000, 
5TRDATA SPANF 70.000, ZCG 0 .000, SVCAW » , 
i.'KHACH 
0. BSO, DELHP = 5000.000, PELMP 0.20O, ITAIX. i, 
DESLP 6 007. HMAXP = 50000.000, HMrNP = o.ooo. I. 1, 
4AX ai o • '0, SMHAXP 1.100,
 SMMINP 
= 0.200, i, 1, 
TIMTOl 5. 500, TIKT02 - O.S00, OLTLF • ).000, I , i. 1, 
WCDMBP ( oio. WPTEAP 900.000, NFUEL -182724! .000, 
XEZ9C 3. 000, IBREG -
a, IPLOT s, IPi"-7.E -3, T PRINT - 0, JFSTOl * 3 , IALV = t, IALP 2, 1COD - 1, IPST02 2 , KERJiDR 2. KMPROP = 1, I PLOT I. HALF 10, NHDTL -
NCR'JSE 2 , NLEGCL = 0, NLEGLO 
0, ALtN o.ooo, -.000, 2 . ooo, 
Nov 18 96 15:08:58 CI7-
3 000, 4 000, 6.000, 
B 000, 10 ooo. 12.000, 
14 000, ALTV 0 000, 0,000, 
0 ooo, 0 000, o.ooo, 
0 000, 0 000, 0.000, 
30000 000, 30000 000, CLINPT 0.000, 
0 000, 0 000, o,ooo, 
0 000, 0 000, o.ooo, 
0 000, 0 000, o.ooo, 
SMN 0 400, 0 500, 0.600, 
0 700, 0 800, 0.900, 
0 700, 0 800, 0.850, 
0 900, ISTRS 0, 0, 
0, 0, 0, 
0, 0, 0, 
0, 0, ITB 0, 
0, 0, o, 
0, 0, 0, 
0, 0, 0, 
ITS 0, 0, 0, 
0, 0, 0, 
0, 0, 0, 
0, 
SEND 
$ADRAG 
ICDO 0, CDBMB 0 000, 0.000, 
0 000, 0 000, 0.000, 
0 ooo, 0 000, o.ooo, 
0 000, 0 000, CDONPT 0.000, 
0 000, 0 ooo, o.ooo. 
0 000, 0 000, o.ooo, 
0 000, 0 000, 0.000, 
CDSTR 0 ooo. 0 000, o.ooo, 
0 ooo, 0 000, 0.000, 
0 000, 0 000, 0.000, 
0 000, CDTNK 0 000, 0.000, 
0 ooo, 0 000, o.ooo, 
0 000, 0 000, o.ooo, 
0 000, 0 ooo, CDEXTR 0.000, 
0 000, 0 000, 0.000, 
0 000, 0 000, 0.000, 
0 000, 0 000, 0.000, 
SMNCDO = 0 000, 0 ooo, o.ooo, 
0 ooo. 0 000, o.ooo, 
0 000, 0 000, 0.000, 
0 000, SMNBMB 0 000, 0.800, 
0 900, 0 930, 0.950, 
0 980, 1 000, 1.100, 
l 400, 1 600, SMSTRS 0.000, 
0 800, 0 900, 0.930, 
0 950, 0 980, 1.000, 
I 100, 1 400, 1.600, 
SMTANK = 0 000, 0 ooo, o.ooo, 
0 000, 0 ooo, 0.000, 
0 ooo. 0 ooo, o.ooo, 
0 000, SMEXTR 0 D00, 0.800, 
0 900, 0 930, 0.950, 
0 980, 1 000, 1,100, l 400, 1 600, SEND SATAKE 
CLLAND -l 000, CLT0 -1 000, DELFLD 45.000, 
DELFTO = 25 000, DELLED 30 000, DELLTO = 10.000, 
LDLAND -1 000, LDTO -1 ooo, 
SEND 
SAPRINT 
ECHOIN 1, ECHOUT = 0, INTM 0, 
C17 -SHORT-ACS YNT-IN 
IPBLNT = 0, 
IPEXT = 0, 
IPINTF = 0, 
IPWAVE = 0, 
SEND 
***•> C-17 PROPULSION MODULE 
3 
SLEWIS 
TWOAB = 40700,0, 
IPCAN 
IPFLAP 
IPLIFT 
KERROR 
0, 
0, 
0, 
0, 
I PENG 
IPFRIC 
IPMIN 
USING CF6 ENGINE (CYCLE ANALYSIS) 
AENDIA 
BA = 5 . 
SCPR 
YREN 
MODPRT 
ALTD 
XMACH 
SEND 
SAFTBD 
SEND 
6.21, AENLE = 15.5, AENWT = 4200.0, 
, IPR = 1, SFADP = 1.4, SFADSP =1.4 
WCWA1 = 0.O3O, 
EN = 4, 
NAB - 6, 
10000.000, 
40000.000, 
0.400, 
0.750, 
1.350, 
95.000, 
1, 
0.000, 
30000.000, 
0. 
0, 
.200, 
, 650, 
KT5 = 0, KODE = 2, 
SFBPP = 1,4, ETAF1=0.90, 
XMDES = 1.400, 
KT7 = 0, 
NDTAIL = 6, 
20000.OOO, 
50000.000, 
0.500, 
0.800, 
Nov 18 96 
15:09:01 
ccccccc ooooooo PPPPPPP EEEEEEE SSSSSSS C 0 OP P E £ 
C O 0 P P E S 
C 0 0 PPPPPPP EEEE SSSSSSS 
C OOP E S 
C P
ccccccc ooooooo p EEEEEEE sssssss 
CONTROL PROGRAM 
FOR 
ENGINEERING SYNTHESIS 
TITLE 
MCDONNELL DOUGLAS C-17 TRANSPORT MISSION ****** 
CARD IMAGES OF CONTROL DATA 
CARD IMAGE 
1) $ DATA BLOCK A 
2) •«** MCDONNELL DOUGLAS C-17 TRANSPORT MISSION ***** 
3) $ DATA BLOCK B 
4) 1 0 0 0 0 
5) S DATA BLOCK V 
6) END 
TITLE; 
**** MCDONNELL DOUGLAS C-17 TRANSPORT MISSION ****** 
CONTROL PARAMETERS; 
CALCULATION CONTROL, NCALC = 1 
NUMBER OF GLOBAL DESIGN VARIABLES, NDV = 0 
NUMBER OF SENSITIVITY VARIABLES, NSV - 8 
NUMBER OF FUNCTIONS IN TWO-SPACE, N2VAR = 0 
NUMBER OF APPROXIMATING VAR. NXAPRX = 0 
INPUT INFORMATION PRINT CODE, IPNPUT = 0 
DEBUG PRINT CODE, IPDBG = c 
CALCULATION CONTROL, NCALC 
VALUE MEANING 
C17-SHORT-ACSYNT.OUT 
1 SINGLE ANALYSIS 
2 OPTIMIZATION 
3 SENSITIVITY 
4 TWO-VARIABLE FUNCTION SPACE 
5 OPTIMUM SENSITIVITY 
6 APPROXIMATE OPTIMIZATION 
ESTIMATED DATA STORAGE REQUIREMENTS 
REAL 
INPUT EXECUTION 
9 9 
INTEGER 
AVAILABLE INPUT EXECUTION AVAILABLE 
5000 1 1 1000 
AAAAAAA CCCCCCC SSSSSSS Y Y N N 
A A c s Y Y NN N 
A A c s Y Y N N N 
AAAAAAA c sssssss Y N N N 
A A c s Y N N N 
A A c s Y N N 
A A ccccccc sssssss Y N N 
T 
T 
T 
T 
T 
T 
NASA-AMES PROGRAM 
FOR 
AIRCRAFT SYNTHESIS 
TITLE 
*«** MCDONNELL DOOGLAS C-17 TRANSPORT MISSION ***»*« 
AIRCRAFT TYPE - TRANSPORT 
1 TITLE: 
'*** MCDONNELL DOUGLAS C-17 TRANSPORT MISSION ****** 
AIRCRAFT TYPE - TRANSPORT 
CONTROL PARAMETERS: 
READ CONTROL, MREAD = 5 
EXECUTION CONTROL, MEXEC = 3 
WRITE CONTROL, MWRITE = 5 
NUMBER IDENTIFYING CONVERGENCE 
VARIABLE FOR CONVERGED VEHICLE, IOBJ = 570 
NUMBER IDENTIFYING COMPARISON 
VARIABLE FOR CONVERGED VEHICLE, JOBJ = 585 
C17-SHORT- ACS YNT-OUT 
SUMMARY OUTPUT PRINT COPE, IPSI.W 
GLOBAL ERROR PRINT CODE, KG LOB P 
GLOBAL COMMON INITIALIZATION COOS, INIT 
DEBUG PRINT CODE, IFBBG 
GLOBAL PLOT CONTROL, IGHJ.T 
DATA TftAKSFER INFORMATION FILE, IRDDTR 
DATA TRANSFER INFORMATION PRINT, IPDTR 
VtH:Ci.E CONVERGENCE INFORMATION : 
COUVERGENCt: TOLERANCE, TOL ^ .1OO00E-03 
t.STIN WCALC VS NEXT S^OPE - .aQOQOE+00 
BOUNDING WEIGL'T, WGMAX = . 850OOF.+06 
MODULE 1LENT'FTCATION NUKSERS: NUMBER moduli; 
1 (JSOmETRY 
2 TRAJECTORY 
3 AERODYNAMICS 
4 PROPULSION 
5 
STABILITY /IWD CONTROL 6 KIK1 IJH'I'S M SONIC BOOM 
9 eeoMQmCfi . 
11 SUMMARY OUTPUT 
14 
TAKEOFF AND LANDING 
OINITIAL ESTIMATES 
if code = l, vnttatrr is fixed 
MODULES Al:;-: CALLED FOR INPUT IN THE FOLLOWING ORDER: 6
 12 3 4 
MODULES ARE CAL)..-:.V FOR EXECUTION IN THE FOLLOWING ORDER; 
12 6 
MODi.I.IRS ARE CALLED FOR OUTPUT IN THE FOLLOWING ORDER: 
6 2 3 4 1 
Inpuh. Ear Moaule # 6 
+ + (FI l *****TT*^ + ^**F • ***** & + l 
1 INITIAL WEIGHTS INPUT DATA 
ACSYNT MODULE NUMBER 6 
)• ' RCRAFr ' ;: TRANSPORT TITLE: »*•* MCDAC C-17 TRANSPORT ****** OCOMTROL OPTIONS 
IPRJMT -
IBELT = Kl = 
K5 KB 
FR 
STRESS = 
DPCABIN = 
IMNTEN = 
TECKJ 
SLOPE[1) = 
SLOPS 19 I -¬ 
SLOPE lilt* 
1 IG-I-J; 11 
0 JOBLIQ 
1.00 K2 
l.OC K6 
.00 KP1 
1.00 TECHG 
3 0000. 
( 
.0 
uO 
•ro oo 
I GEAR 
1 KTGR 
1 . 00 
i .00 
1 . 00 
1 I TAIL = 
0 KWING = 
1.00 Kj = 
1.00 AT MACH = 
.OO KP2 = 
1 . OO WOTO = 
DENS 
1 JFLTYP 
1 
.00 
.00 . 30 
0 K ERROR 
0 KS0»Y 
1.0 K4 
.85 MAXIT 
. 00 
530000. 
. :0O 
» 1 
0 
1 
1.0 
1 
FLIFTF = .000 
00 
00 0L 
00 
00 
oo 
0" o -Vv 00 
09 
00 
00 i.oo 
1 .00 
QUANTIT'i 
VALUE CODE QUANTITY VALUE COD 
WAF 174000. 0 WAIRC 5800 , 0 
WAPU 232 . 0 V.'AMMUH = 0. 0 
WARM 0. 0 WBAG = 17400. 0 
WE El = 0. 0 WBODY 69600. 0 
IICAHD = 0 . 0 WCARGO = 124000. i 
WCREW 1500. 1 WE = 31BOO. 0 
WELT = 5320. 0 WEP 29000, 0 
'. • ANK 3 . 0 WFEQ = 81200. 0 
HFS 4060 . 0 WCA = i?40 . p WGEAR 0. 0 WHDP S 4640 . 0 WKT 4640. 0 WINST = 2900 . 0 
WLG — 29000. 0 WMISS = 0. 0 
WNA 5800 . 0 WPA 34800. 0 
V.'PASS 
- 1:7000 , 0 WPL s 104100. 0 WPS - 46100. 0 WSC 11600. 0 
KTSUM = 580000. 0 WVT S80O, 0 WWTNG = 46100. 0 llOmb 0. 0 WSNVP * . 0 WPIV 0 . 0 
WLIFTF 0 WBS2 - 0. 0 
WTHRV O. 0 
input, Module 1 1 
,. r * • * * * * * * ************* ********* * * ********** * * * * + Geometry Inpu- D^ita 
1*'*" MCDONNELL T30UGLAS C-17A TRANSPORT GEOMETRY 
2 SWING AR 
LFLAPC 
TCROOT 
6 WFFRAC 
7 KSWSEP 
8 SEND 
9 SHTAIL 
10 AR 
11 SWES'P 
12 TCTIP 
13 K ..: ••• 
14 SEND 
15 SVTAIL 
16 AR 
17 SWEEP 
1 3 TCROOT 
7.200, AREA 
0.110, SWEEP 
0.135, TCTIP 
0.800, XWING 
1, 
5.000, AREA 
27.000, TAPER 
0.080, XHTAIL 
1, 
1.000. AREA 
J1.000, SWFACT 
0.110, TCTIP 
3800.000, 
25.000, 
0.107, 
0.290, 
D:H>:o 
TAPER TFLAPC 
ZROOT 
845.000, 
0,400, 
-0.010, 
CVHT 
TCROOT 
ZROOT 
685.000, 
1.000, 
0.110, 
CWT 
TAPER VINO 
-6.000, 
0.300, 
0.170, 
0.800, 
1.000, 
0.090, 
1.765, 
0.1DO, 0,990, 
1.000, 
JNIIV 13 96 C17-SHORT-ACS YNT-OUT 
33 86 10.53 348 34 
19 XVTAIL 0 871, YROOT = 0 000, ZROOT 0 900, 4C 26 10 .53 348 34 
46 66 10. 53 348 34 
20 KSWEEP 1, 53 06 10.53 348 .34 
59 46 10 .53 348 34 
21 SEND 65 86 10.53 348 34 
72 26 10.53 348 34 
22 SWPOD 78 66 10.53 348 34 
85 06 10 .53 348 34 
23 DIAM 10 000, LENGTH 10 ooo, X = -0 750, 88 84 10.63 355 01 
92 63 10.69 359 07 
24 Y 0 301, 2 = 0 230, SWF ACT = 1 000, 96 41 10 .71 360 47 
100 19 10.69 3 59 18 
25 $END 103 97 10.63 355 15 
107 75 10. 53 348 40 
26 SWPOD 111 53 10.39 338 94 
115 31 10 .20 326 80 
27 DIAM = 10 000, LENGTH 10 ooo. X -1 000, 119 09 9.97 312 05 
122 87 9.69 294 77 
28 Y = 0 591, Z 0 230, SWFACT = 1 000, 126 65 9.36 275 05 
130 43 8.97 253 04 
29 SEND 134 21 8.54 228 89 
137 99 8.03 202 82 
30 $FUS 141 77 7 .46 175 05 
145 55 S.81 145 86 
31 BDMAX 21 060, BODL = 160 670, FRAB 3 590, 149 33 6.07 115 60 
153 11 5.19 84 63 
32 FRATIO 0 000, FRN 1 000, 156 39 4.12 53 26 
160 67 2 .40 18 10 
33 SEND Fuselage 
Max 21.060 
34 SENGINE Fineness Ratio.. 7 . 629 
Surface 9511.863 
35 DIAM 8 000, N - 4, OUTCOD = 3, Volume.. 45999,004 
36 SEND Geometry Initial Output 
END OF GEOMETRY DATA CARDS 
3 6 LINES READ 
Geometry Initial Output 
Fuselage Definition 
X R Area 
00 00 00 
1 05 1 84 10 61 
2 11 3 03 28 85 
3 16 4 03 50 92 
4 21 4 89 75 24 
5 26 5 66 100 80 
6 32 6 35 126 87 
7 37 6 98 152 87 
CO 42 7 53 178 35 
9 48 8 04 202 92 
10 53 8 49 226 26 
11 58 8 89 248 09 
12 64 9 24 268 18 
13 69 9 55 286 34 
14 74 9 81 302 39 
15 80 10 03 316 20 
16 85 10 21 327 65 
17 90 10 35 336 65 
18 95 10 45 343 13 
20 01 10 51 347 04 
21 06 10 53 348 34 
27 46 10 53 348 34 
Dimensions of Planar Surfaces (each) 
Wing H. Tail V, Tail Canard Uni ts 
NUMBER OF SURFACES 1.0 1.0 1.0 1.0 
PLAN AREA 3 8OO.0 845.0 685 .0 .0 [SQ.FT, 
SURFACE AREA 6779.8 1696.1 1135.6 .0 (SQ.FT. 
VOLUME . 7652.7 704 . 6 1380.5 ,0 (CU.FT. 
SPAN . 165 .409 65 .000 26 .173 .000 (FT. ) 
L.E. SWEEP 28 .418 30 .763 41 .082 .000 (DEG.) 
C/4 SWEEP 25 .000 27 .000 41 , 000 .000 (DEG,) 
13 . 601 14 .165 40 .753 .000 [ DEG. ) 
ASPECT RATIO . , 7 ,200 in .000 1 .000 .000 
ROOT CHORD 35 .344 18 .571 26 .304 ,000 (FT. ) 
ROOT THICKNESS 57 .257 20 .057 34 .721 .ooo (IN.) 
ROOT T/C .135 .090 , 110 .000 
TIP CHORD 10 . 603 7 . 429 26 .041 .000 (FT . ) 
TIP THICKNESS 13 ,614 7 . 131 34 .374 .000 (IN. ) 
TIP T/C .107 .080 .110 ,000 
TAPER RATIO .. 3 00 .400 . 990 .ooo 
MEAN AERO CHORD... 25 . 194 13 .796 26 . 173 .ooo (FT. ) 
LE ROOT AT 37 .758 135 .071 113 .640 .000 (FT. | 
C/4 ROOT AT . 46 594 13 9 .714 120 .216 .000 (FT. | 
TE ROOT AT 73 102 153 .643 139 . 944 .000 (FT. ) 
LE M.A.C, AT , 56 .118 143 .362 125 .029 .000 (FT. ) 
C/4 M.A.C. AT 62 .416 146 .811 131 ,572 .000 (FT. ) 
TE M.A.C. AT 81 311 157 ,158 151 202 .ooo (FT. ) 
Y M.A.C. AT 33 930 13 . 929 13 064 .000 
LE TIP AT . 82 509 154 .416 136 .457 .000 (FT. ) 
El 
Nov W 96 
15:09:01 C17-SH0RT-ACS YNT-OUT 
C/4 TIP AT. 
TE TIP AT.. 
ELEVATION.. 
85.160 156.274 142.967 
93.112 161.845 162.498 
8.424 29.499 9.477 
GEOMETRIC TOTAL VOLUME COEFF 
EFFECTIVE TOTAL VOLUME COEFF 
EXTENSIONS 
,745 
.745 
.075 
. 075 
.000 IFT.) 
.000 (FT.) 
.000 (FT.) 
.000 
.000 
CRUISE .75 .75 28000 -1 500.0 .0 .0 .0 1.0000 1 4 0 0 0 0 0 
Centroid location at .00 
Area .0
Sweep Angle .0
Wetted Area 0 
Volume .0
Total Wing Area 3800.00 
Total Wetted Area 22219,92 
Strake Rear Extension 
.00 
.00 
.00 
.00 
input for Module tt 3 
*********************************************************** 
1 AEKQDttlAHlC INPUT DATA 
** MCDAC C-17A TRANSPORT AERODYNAMICS MODULE ** 
FACTORS INTEGERS AND LOGICALS REALS 
FALEL = 1 .000 ALELJ = 3 NALF 10 ABOSB 220 SHK 
FUEL TANKS = 25 000 
Tank Volume Weight Density FBLNT = . 010 IALF = 0 NMDTL = 6 ALMAX = 20 ooo SM 
Wing 5292 264612. 50 . 00 + = 000 
Fus#l 0 0. 50 .00 FCD = 1 .ooo IALP = 2 ECHOIN = 1 AKC 35 000 SMNDR 
Pus#2 0 . 50.00 + = 860 
Total 264612. 
+ 
FCDF 
X = 60 000 
1 .000 IAXE c ECHOUT = 0 BTEF 1 ooo SWPMA 
Mission Fuel Required = 91184 , FCDL = 1 .000 ICDO = 0 ELLIPC = F CGM 250 •SWPMI 
Available Fuel Volume in Wing 6815. N = 000 
FCDLH = 1 ,000 ICOD 1 ELL1PH = F CLLAND = -1 ooo YO 
Aircraft Weight - 580000.000 lbs. 4 = 000 
Aircraft Volume = 55736.773 cu.ft, FCDO = 1 .ooo INORM = 1 ELLIPW = F CLTO = -1. 000 ZCG 
Aircraft Density - 4 .764 lbs./cu.ft. + 
FCOW 
000 
1 .000 INTM _ 0 CSF _ 1 000 
ICASE = 4 (Fineness Ratio Method) FCDWB = 1 .000 IPBLNT = 0 DELFLD = 45 ooo 
FCL 1 .000 I PENG = 0 DELFTO = 25 ooo 
FCLH 1 .ooo IPFRIC = 0 DELLED = 30. ooo 
FDNOSE = 1 .000 IPTEXT = 0 DELLTO = 10. 000 
Input for Module tt 2 FENG 1 .000 IPINTF = 0 ESSF = 1. ooc 
HI.).,,,,..,.... ************ ***************** ********** * * * ** ** .* * FEXP = .780 IPLIFT 0 EXA = 667 
TRAJECTORY INPUT FINTF = 1 .000 I PLOT - 1 EXC 2 ooo 
FLBCOR = 1 .ooo IPMIN = 0 IT ooo 
FLD = 1 .000 IPWAVE = 0 LDLAND -1 . 000 
TIMTOl =5.5 MENDUR = 0. NCRUSE = 2 I PLOT = 2 FLECOR 1 . 000 ISMNDR = 0 LDTO = -1 . 000 
TIMT02 = .5 QMAX = 800. IPSIZE =-3 HMINP = 0 FLNOSE = 1 .000 ISUPCR - 0 MACHN = 750 
FRFURE = .05 XDESC = 80.0 IPSTOl = 3 HMAXP - 50000 FLSCOR = 1 .000 I TRAP = 0 QHOCjl = OOC 
DESLF =6.00 WKFUEL = 1.000 IPST02 = 2 DELHP = 5000 . FMDR = 1 .010 IVCAM = 0 RCLMAX = 1. ooo 
ULTLF =9.00 CRMACH = 990 IBREG = 0 SMMINP = .200 FSEP = 1 .000 IXCD = 1 ROC = 015 
RANGE = 1000. WKLAND = 570 IENDUR = 0 SMMAXP = 1 ,100 FTRIM = 1 . 000 KERROR = 0 SFWF = 1. ooo 
WFUEL = 182720. FLFAC = 600 IPRINT = 0 DELMP = .200 
WFEXT = 0. DECEL ^ 250 KERROR = 2 WCOMBF = 01 
WFTRAP = 900. NLEGCL = 0 NLEGCR ^ 0 NLEGLC = 0 ARRAYS 
FWGMAX = 1.200 TOL = 001 MILCOM = 0 NMISS = 1 
NCODE = 0 ALIN = .ooo 1.000 2 . 000 3 000 4.ooo 6.000 8.000 10 .000 12 .000 
MMPROP = 1 + 14.000 
ALTV = 0. 0. 0. 0. 0. 0. 0. 3 30000. 
* 30000. 
CDBMB = . oooo .0000 .oooc .oooo .oooo .oooo . 0000 oooo oooo 
MISSION 1 + .0000 
CDEXTR = .0000 . OOOC . oooo .0000 .0000 .0000 .oooo oooo oooo 
MACH NO. ALTITUDE HORIZONTAL NO. VIND + .0000 
PHASE START END START END DIST TIME TURN "G"S WKFUEL M IP IX B A P CDONPT .0000 .oooo .0000 .oooo .oooo . oooo .0000 oooo oooo 
,0000 
CLIMB .50 .00 0 10000 .0 .0 .0 2 5O.0 1. oooo 1 2 -1 C 0 0 0 CDSTR = .0000 .0000 ,0000 .0000 .0000 .0000 .oooo oooo oooc 
CLIMB .60 ,00 -1 28000 .0 ,0 .0 310,0 1 . oooo 1 2 -1 0 0 0 0 * . 0000 
CRUISE .75 .75 28000 -1 2000.0 .0 .0 .0 1 . oooo 1 4 0 0 0 0 0 CDTNK = ,0000 .oooo .oooo .0000 .0000 . oooo .0000 oooo oooo 
CLIMB .50 .00 0 1000C .0 .0 .0 250.0 1 . oooo 1 2 -1 0 0 0 0 + .0000 
CLIMB .60 .00 -1 28O00 .0 ,0 .0 310.0 1 , oooo 1 2 -1 0 0 0 0 CLINPT = ooo .ooc ,000 000 .000 .ooc .ooc .ooc .000 
15:09:01 C17-SHORT-ACS YNT-OUT 
4 .000 SFSFC1 = 1.000 SFSFC2 = 1.000 SFSFC3 = 1.000 
CLO . 000 OOC OOO OOO OOC 000 000 000 000 SMI .500 SODG 1.000 TOSA 518.OOC 
+ .000 TR 520.000 TWAB = 0. TWOAB = 40700. 
CLMIN .000 000 000 OOO 000 .000 000 000 000 TWTO = , 500 T3 2800. T5M 3400 , 
4 .000 T51 0. T7M 3400. T71 0 . 
CMO . 000 000 OOC 000 000 000 000 000 000 VC1 .980 WCWA1 = ,030 XMDES = 1 .400 
4 .000 XMT .350 YREW 95. FRBT .OOC 
FCDRA = 1.000 1 OOO 1 000 1 000 1 000 1 000 1 OOC 1 OOO 1 OOO PRPN .000 RDIAM = 1.150 RLENG = 2 .000 
4 1 .000 
FCLRA 1 . 000 1 000 1 OOO 1 000 1 000 1 OOO 1 DOO 1 OOO 1 OOO 
+ 1 . 000 IPR 1 IPRINT = 0 IPLOT = 0 
FLDM 1.000 1 D00 1 OOO 1 OOC 1 000 1 000 1 000 1 OOO 1 OOO KERROR - 0 KODE 2 KT5 0 
4 1 .000 KT7 0 MINPR = 0 NAB 6 
FVCAM = 1.000 1 000 1 000 1 000 1 000 1 000 1 OOO 1 000 1 000 NOZZ 0 NPROP = 6 NSUMM = 15 
4 1 .000 IENG 5 ICF6 ) 
ISTRS 
r 
0 0 0 0 0 0 0 0 0 
ITB 0 0 0 0 0 0 0 0 0 THESE VARIABLES ARE OSED BY TABLE LOOK UP 
T 0 ESF i .OOO HDTAIL 6 IPDBUG - 0 IIPRINT = 0 
ITS = 0 0 0 D 0 0 0 0 0 
D 
ITRIM 1 1 1 1 1 1 1 1 1 ALTD = 0. 10000. 20000. 30000. 40000, 50OOO. 
4 1 XMACH = .200 .400 .500 .650 .750 .80C 
SMEXTR .000 BOO 900 93C 950 980 1. 000 1 100 1 400 XMPRI = .000 ,300 .600 .900 1 .200 4.000 
4 1 . 60C XPRI = i. OOO 1.000 1.000 1 -OOC 1 .000 i. OOO 
SMN .400 500 600 700 800 900 700 800 850 XMPRI1 = .000 .000 ,000 ,000 .000 .000 .000 
4 .900 4 .OOO .000 .000 
SMN 3KB = .000 800 900 930 950 980 1. OOO 1 1O0 1 400 XPRI1 = .000 .OOO ,000 .000 .000 .000 .000 
4 1 .600 + .OOO .000 . 000 
SMNCDO = .OOC OOO 000 000 OOC 000 000 000 OOO XMPRI2 = .000 .000 .000 .000 .000 .OOO .000 
4 .000 4 .OOO .000 .000 
SMNSWP - .000 000 OOO 000 OOO 000 000 000 OOO XPRI2 = .000 .000 .000 .000 .000 .000 .000 
4 .000 + .000 .000 .000 
SHSTRS = .000 800 900 930 950 980 1. 000 1 100 1 400 
4 1 . 600 
SMTANK = .000 OOC OOO OOO 000 000 OOO OOO 000 
+ .000 *********** ******** *********** ********** ********* ********** *********** ******** 
YSWP = .000 000 000 000 000 000 000 000 OOO ** Begin Vehicle Convergenc e ** 
4 .000 
Estimated Gross Weight = .58000E406 
Calling Module # 1 
Calling Module # 2 
Calling Module # 6 
Input for Module 4 Calculated Gross Weight - . 52978E+06 
****** **, ******* .**« * * * * * * * * " -** **** * * A * * * * * * * * * *** * * * * * *.»* **** * * Slope o£ Wcalc vs. West line = .80000E+00 
PROPULSION INPUT 
VERSION 04-76 
•* C-17 PROPULSION MODULE - USING CF6 ENGINE (CYCLE ANALYSIS) 
Estimated Gross Weight = .4O6O0E+06 
Calling Module # 1 
Calling Module # 2 
Calling Module # 6 
Calculated Gross Weight = .46161E406 
AENDIA - 6 210 AENLE 15 500 AENWT 4200 000 Slope of Wcalc vs, West line = .39180E400 
ALTI 000 AM 000 ATURB 385 
AENTW = 000 Estimated Gross Weight = .49743E+06 
AUAENG = OOO AWAENG 157 BA 5 900 Calling Module # 1 
DELPR = OOO DELT57 = 100 000 DEPWCC = 2 000 Calling Module # 2 
DIA1 B 200 EAB1 750 EB1 = 940 Calling Module # 6 
EDI 750 ETAC1 820 ETAF1 900 Calculated Gross Weight = .49735E+06 
ETAT1 = 920 HTR = 300 HVF = 18600 000 Slope of Wcalc vs. West line = .3919OE+O0 
MACH1 = 1 000 MACH 2 1 100 PCDPAC = 1 000 
POSA 29 920 PRFD 1 560 PWCC 100 000 Estimated Gross Weight = .49729E406 
P11P1 = 1 720 P2P1 = 30 OOC R10A = 1 000 Calling Module # 1 
R32 940 R54 = 940 R54N = 920 Calling Module # 2 
R711 980 R711N = 980 SCPR 1 350 Calling Module # 6 
SFADP = 1 400 SFADSP 1 400 SFAUXP = I OOC Calculated Gross Weight = .49729E406 
SFBEP = 1 000 SFBPP = 1 400 SFBTP = OOO 
SFDIVP = 1 000 SFINSP 1 000 SFIP = 1 000 ** End Vehicle Convergence ** 
Nov J8 96 C17-SHORT-ACS YNT-OUT 
3 COMRNRFFWICFL itaratitHft-* Riqjuirod 
CALLINCF MODULE P 1 
CALLING MFLDUL^ # 2 
CALLING MODULE # 6 
OUTPUT FOR MODULE # 6 
2RCIAX: 
DESIGN LOAD FACTOR: 
ULTIMATE LOAD FACTOR: 
^RUCIRURE AND MATERIAL : 
WING £• • S.TION: 
BODY ELATION: 
WEIYHT STATEMENT - TRANSPORT 
MCDAC C-17 TRANSPORT *** 
800 . 
6 . 00 
9 .00 
ALUMINUM SKIN, STRINGER 
SANDERS EQI LA T I •:):"; 
SANDERS E-JU-LION 
COMPONENT POUNDS J CILOGRIME yi ONT SLOPE RECH FIX 
AIRIRAJR.O STRUCTURE 187373 . 84993. 37 68 NC 
WING 81135. 36803. 16 32 1 00 1 00 NO 
PUNNLAGE 57789. 2621J. 11 62 1 00 1 oo NO 
HOTLZINTNL T*IL ( LOW) ' jBJJ . 5395. 2 3S 1 oo 1 oc NO 
VERTICAL TALL 7263 , 3. 14. 1 46 1 00 1 00 NC 
NACFLL1 6024 . 273:,: . 1 21 1 oc 1 00 NC 
LANDING GEAR 23270. 1055^. i 58 1 00 1 00 NO 
PROPULSION 21672. 91 .0. 4 36 NO 
ENGINES { 4) 19992. 150&H,. 4 02 1 oo 1 00 NC 
FUEL SYSTEM 1680. 762 . 34 1 00 1 oo NO 
FIXED EQUIJ -::I^NT 26641. 12034. 5 36 1 oo NO 
HYD ix PNEUAIATIC 2984 , 13S3 . 60 1 oo NO 
1 :<_•• RIR-AL 3799 . 1723 . 76 1 00 NC 
AVIONICS 1835 . 832 . 37 1 00 NO 
INSTRUMENTATION 1041 . 472 . 21 1 OC NO 
DE-ICE & AIR COND 0. oo 1 00 NO 
AUX POWER SYSTEM 6', J . I« 1 00 NO 
FURNISH & EQPT 122S3. 5574, 2 47 1 00 NO 
S^ATS AND LAVATORIES 0 . 0. oo 00 NO 
GIIIIY 0. 0. 00 1 00 NO 
MISC CC~K. IT 0 . 0 . 00 00 NO 
CABIN FINISHING 6620 . 3003 . 1 33 1 OO NO 
CABIN F.TIERGENCY EQUIP 9 . 0 . 00 1 00 HO 
CARGO HANDLING 5669 . 2571 . 1 14 1 oo NO 
FLIGHT CONTROLS 4021 . 1824 . 81 1 00 NO 
EMPTY WEIGHT 235686. 106907. 47 39 
OPERATING ITEMS 0. 0. 00 NO 
FLICRHL CREW ( 0) 1500 . 580 , 30 ¥•:: 
CREW BAGGAGE AND PROVISIONS 25 . 11 . 01 HE 
FLIGHT ATTENDENTE i 0) 0 . 0. op NO 
UNUSABLE FUEL AND OIL 9 00. 408. P NC 
PASSENGER SERVICE 0. • 3 NO 
CARGO CONTAINERS 19840. 8999 . 3 99 NO 
OPERATING WEIGHT EMPTY 257951. 117007. 51. 87 
115337. 52317. 23 19 
i'Tiy LOAD 124000. 5621 , . 24 . 94 NO 
PASSENGERS 
SIIGGJGE 
Calculated Wei-IHT 
Estimated Weight 
Percent Error 
( 0) 
0. . 
56216. 
.00 
.00 
24 . 94 124000. 
497388. 225570. 100.00 
197289. 225570. 
Kr. 
YES 
No 
Nov IS 96 
ismm CL7-SH0R T-ACSYNT-OUT 
. .... It for Module tt 2 
******* * * * * * * *********** ********* * * * * • *»* ********* T T • • • ********** 
TRAGEC1CRY 
OU' '.T MISSION 1 (PAYLOAD = 124000. LB) 
FUASE M H CL ALPHA WFUEL (K~ VEL 
SFC(I) TKEirSTm CD D uMMA W WA Q 
sFcru) iu) CDIN5T L/D TUB/ TIL IT/; X 
WARM-UP 0. 4902.8 5 , 50 
33 162800. 
TAKEOFF .25 0 . 2 . 0256 12 . 00 450.1 . 50 278 . 
. 41 133707. .4557 3 . 00 4919.14,5 1411 .92 92 . 
.41 133707. .0030 4 .45 1.00 1 . 00 5196, 
2ND SEC- .25 4 0 0 . 2.0256 12 .00 278 . 
.41 100280. . 4557 6 . 91 491936.5 1411 . 92 92 . 
.41 133707. .0030 4 .45 1 .00 . 00 
CLIMB . 46 10000. . 6070 5 .35 2067.7 2 . 56 •191 . 
. 50 89427. .0377 6 .91 !: il s
 6 8 . 9 
1096 .13 212 . 
Cycle .49 90853. .0018 16 .09 1 . 00 1 . 00 12 . 
CLIMB .82 28000, .4009 2 .81 5022.7 a .55 825 . 
. 65 48 • 1 . .0332 . 84 484846.2 721 .40 326. 
Cycle , 63 49995 .0014 12 1 .00 1 .00 64 . 
CRUISE . 75 280C0. .4107 3 .06 75593.4 258 .96 753 . 
. 65 25759. , 0250 .oo 40S852,8 586 .00 271 . 
cycle . 62 27165. . 0014 16 . 44 . 53 1 .00 1924 . 
CLIMB ,46 100OD. .5027 A .38 1588.4 1 .97 491 
. 50 i : 7 .' . . 030B 9 .12 407264.5 109 6 . 13 212 . 
Cycle .43 908S3. , 0013 16 .31 1.00 1 .00 9 . 
CLIMB .82 28000. .3239 2 .25 3431.3 5 .77 825 . 
.65 4S237. . 0301 1 55 403833.2 721 40 -••26. 
Cycle .63 49995. . 0014 10 76 1 . 00 1 00 43 . 
CRUISE .75 28000. 3798 2 .82 16388.6 60 .35 753. 
. ii 24308. .0236 00 387444.6 582 .34 271. 
Cycle . o3 25710. . 0014 16 09 .50 1 00 448 . 
LAND!NG .22 0 . 2.5935 12 00 2 50. 
.40 136692. .9724 18 .47 431547.3 1401 .74 74 . 
.40 137607. . 0033 2 67 1.00 1 00 6201 . 
Landing Field Length (ground run) Height fg.r Landing caiculaxIon Lanjjiiu Thrust to Weight ratio Takeoff Weight 
Landing Weight 
3027. ft 431547. lbs 
.317 
497239. lbs 
3B7445. lbs 
Fuel Summary --i-al
 Fuel = 116237, Takeoff Fus". : Fuel Load: Hi3si;i«
 Vuel - I0»fi45. Wsnsup 4903. External - 0. 
Reserve Fue 1 - 5492. TakeoTf = 450. Internal = 116237. Trapped Fuoi = 900. fllouk
 'J'inw - 5.736 hrs 
5lock Ranye = 2500.0 n.m. E*.ln~k
 fuel  109844.8 lb, 
TakeoLI Field Length [total ru.'ii = S I ' G . ft 
Landing Field Lrnigth (total rur. = 6201. ft Decel 4 .250 Gs 
Nov IS 96 
15:09.01 C17-SHORT-ACS YNT-OUT 
Output for Modult | 3 
l>e tailed Aert*Iynj±mioutp*j; 
Mach - . 8b 
Altitude = 3 0000. Takeoff Coiitigurjtion: aps and Slats 
Par; lite Drag 
Friction 
1 us 
Body 
2 
Wing 
2 
STRAKES 
2 
H. Tail 
2 
V. Tall 
2 
Canard 
2 
InL^rf rjrenre 
3 
Wave 
3 
F.x'f ^riin ]. 
4 
Tanks 
4 
Bombs 
.-.'i "res 
. .. ra 
CnTTber 
.0111 
. 00 ' 
.0038 
.0000 
.0014 
. 0008 
.OOOO 
. 0031 
. 0266 
. 0000 
. oooo 
.oooo 
.oooo 
.0000 
. oooo 
Indiittd Drag 
Alpha CI 
.0 .784 
1.0 .934 
2.0 1.078 
3.0 1.220 
4.0 1.357 
S.O 1.621 
8.0 1.614 
10.0 1.772 
12.0 1.705 
14.0 1.792 
Cd 
.2249 
.2418 
.2792 
,3004 
.3470 
.3777 
.4558 
.4814 
. 5702 
L/D 
3 . 5 
3 .9 
4.2 
4.4 
4 . 5 
4 .7 
A.3 
3 . 9 
3 .5 
3.1 
Cm 
.000 
.000 
.000 
.000 
. ooo 
. 000 
.000 
.ooc 
.000 
,OON 
e Cdtrim Deltrim 
.15 
. 19 
. 23 
.28 
.31 
.38 
.34 
.33 
.29 
.27 
.0050 
. 0067 
.0037 
.0109 
. 0132 
.0171 
. 0137 
.0189 
.0262 
.0366 
-4.3 
-5.1 
-6.0 
-6.9 
-7.7 
-9 . 4 
-9.6 
-11.1 
-13 .0 
-15.0 
Cdmin 
ft 
. 0407 
Slope Factors 
Cl/Alpha (PER radial-.) 4.1726 
Cdl/Cl"2 .1649 
Alpha Transition Zone 2-3 7,165 
Flap Setting 2!. 
Slat Set ting 10
Flap Type Single 519. so; 
Mach = .90 
Altitude = 30000. 
Parasite Drag 
T'riction .0110 Alpl ia CI 
Sons 
Body . 0050 0 1 293 
+ 2 
wing .0038 1 0 1 456 
+ 2 
Strakes .0000 2 0 1 613 
+ 2 
H. Tail . 0013 3 0 1 767 
+ 2 
v. TIN. .0008 4 C 1 917 
+ 2 
Canard . oooo 6 0 2 206 
Interference .0023 8 0 1 721 
+ 4 
Wave , 0719 10 0 1 853 
Fxtemal .O00D 12 0 1 972 
T=inks . oooo 14 0 2 082 
4 
Bombs . 00 " 
SroreH .oooo 
Extra ,oooo 
Landing Configuration: 
Indnr-ed Drag 
Cd 
.6474 
. 67 88 
.7093 
.7411 
.7740 
.B41B 
.SS98 
. 639S 
.72H9 
.82B9 
Flaps and Slats 
L/C 
2.0 
2 . 1 
2.3 
2 . 4 
2 . 5 
2 . 6 
3 . 1 
2 .9 
2.7 
2 . 5 
Cm 
. ooc 
.000 
. ooo 
. ooo 
.000 
000 
.000 
.00 3 
. 000 
.000 
. 13 
.16 
.18 
.21 
. 24 
.28 
.28 
. 27 
.27 
.26 
Cdtrim Deltrim 
.0130 -t,M 
. 0155 
.0183 
. 0211 
.0241 
. 0302 
. 0154 
. 11214 
.0293 
. 0400 
-7.6 
-8.4 
-9 .2 
-10.0 
-11 . 6 
-10 .0 
-11.6 
-13 .4 
-15 . 4 
Slnpe Factors 
CI'Alpha (per radian) 3.2262 
Cdl'Cl~2 .1716 
ftlph* Transition Zune 2-3 6. 514 
Nov IS 96 
l5:U9;tH 
Camber 
CDMIN 
FT 
. oooo Flap Setting 
Slat Setting 
Flap Type 
C17-SHORT- ACSYNT-OUT 
Detailed Aerodynamics Output 
Single 
45 . 
30 . 
519. sq. Mach = .40 
Altitude = 0. 
Parasite Drag 
Friction 
Zone 
Body 
2 
Wing 
2 
Strakes 
2 
H. Tail 
2 
V. Tail 
2 
Canard 
2 
Interference 
2 
wave 
2 
External 
2 
Tanks 
2 
Bombs 
Stores 
Extra 
Camber 
.0118 
. 0053 
.0041 
. oooo 
.0014 
.0009 
.0000 
. 0042 
.0000 
.0000 
.0000 
.0000 
.0000 
.0000 
.oooo 
Cdmin 
ft 
Mach = 
Altitude = 
Parasite Drag 
Friction 
Zone 
Body 
2 
Wing 
2 
Strakes 
2 
H. Tail 
2 
V. Tail 
2 
Canard 
2 
Interference 
2 
Wave 
2 
External 
2 
Tanks 
3 
Bombs 
Stores 
Extra 
. 0160 
.50 
0, 
Induced Drag 
Alpha Cl Cd L/D Cm e Cdtrim Del trim 
.0 .000 .0160 0 .000 .00 .0000 . 0 
1 . 0 118 . 0168 7 0 . 000 .76 .0001 - .8 
2 .0 233 .0192 12 1 ,000 .75 .0004 -1. 6 
3.0 .345 .0230 15 0 .000 .75 .0008 -2.4 
4.0 454 .0282 16 1 .000 .75 . 0014 -3.1 
6.0 665 .0424 15 7 .000 .74 .0030 -4 . 6 
8.0 867 .0611 14 2 .000 .74 .0052 -6.2 
10 .0 1 060 .0840 12 6 .000 ,73 .0077 -7,7 
12 .0 1 246 ,1107 11 2 ,000 .72 .0107 -9.3 
14 ,0 1 424 .1410 10 1 . ooo .72 .0140 -11 .1 
Slope Factors 
Cl/Alpha (per radian) 
Cdl/Cl-2 
Alpha Transition Zone 2-3 
Programmed Flap Setting 
Flap Type Single 
5 .8299 
.0616 
16.894 
0. 
519. sq. 
Induced Drag 
0116 Alpha Cl Cd L/D Cm E Cdtrim Deltrim 
0053 0 000 .0159 0 .000 .00 . 0000 .0 
0040 1 0 121 .0167 7 3 . 000 ,76 .0001 -.8 
oooo 2 0 240 ,0192 12 5 .ooo .76 .0004 -1 .7 
0014 3 0 355 .0232 15 3 . 000 .76 . 0009 -2 .5 
0009 4 0 4 68 .0287 16 3 .000 .76 .0015 -3.3 
0000 6 0 685 .0436 15 7 .000 .75 .0033 -4.9 
0042 8 0 892 .0632 14 1 , ooo .74 .0056 -6.4 
0000 10 0 1 090 .0872 12 5 .000 .74 .0084 -8.1 
oooo 12 0 1 280 .1150 11 1 , 000 ,73 . 0116 -9.8 
oooo 14 0 1 433 .3257 4 4 .ooo .29 .0161 -11 .8 
oooo 
oooo 
oooo 
Slope Factors 
Cl/Alpha (per radian) 
Cdl/C1^2 
5.8634 
. 1509 
Alpha Transition Zone 2-3 13.323 
Nov IS 96 
15.09:01 C17-SHORT-ACSYNT-OUT 
Camber 
Cdmin 
Et 
.0159 
Programmed Flap Setting 
Flap Type Single 
0. 
519. SQ. 
Detailed Aerodynamics Output 
Mach = 
Altitude = 
Parasite Drag 
Friction 
Zone 
Body 
2 
Wing 
2 
Strakes 
2 
H. Tail 
2 
V. Tail 
2 
Canard 
2 
Interference 
2 
Wave 
2 
External 
3 
Tanks 
3 
Bombs 
Stores 
Extra 
Camber 
Cdmin 
ft 
.60 
0 . 
.0115 
.0052 
.0040 
.OOOC 
.0014 
.0009 
.0000 
.0042 
.0000 
.0000 
.0000 
.0000 
.0000 
. OOOO 
.OOOO 
. 015E 
Induced Drag 
Alpha Cl Cd L/D Cm e Cdtrim Deltrim 
.0 OOO .0158 0 .000 .00 .0000 .0 
1.0 126 .0167 7 6 .000 .77 . 0001 - .9 
2.0 250 . 0193 12 9 .000 .77 .0004 -1.7 
3.0 370 .0236 15 6 .000 ,77 .0010 -2.6 
4.0 487 .0295 16 5 .OOO .76 .0017 -3.4 
6.0 712 .0453 15 7 . OOC .76 .003 6 -5.1 
8.0 927 .0662 14 C .000 .75 .0062 -6.8 
10.0 1 132 .0916 12 4 .000 .75 . 0092 -8.5 
12.0 1 277 ,2501 5 1 .000 .31 .0125 -10 .4 
14.0 1 407 .3249 4 3 .OOO .28 .0165 -11.7 
Slope Factors 
Cl/Alpha (per radian) 
Cdl/Cl*2 
Alpha Transition Zone 2-3 
Programmed Flap Setting 
Flap Type Single 
5.7573 
.1562 
10.880 
0. 
519. sq. 
Mach 
Altitude = 
Parasite Drag 
.70 
0 . 
Induced Drag 
Friction 
Zone 
Body 
2 
.0113 
.0052 
Alpha 
' .0 
Cl 
000 
Cd 
.0156 
L/D 
.0 
Cm 
. OOO 
e 
, OO 
Cdtrim 
.0000 
Del trim 
.0 
Wing ,0039 1 0 133 .0166 8, 0 . 000 .79 ,0001 -.9 
Strakes 
2 
.0000 2 0 263 .0195 13 5 .000 .78 .0005 -1.8 
H. Tail . 0014 3 0 390 .0242 16 1 .000 .78 .0011 -2 .7 
V. Tail ,0009 4 C 513 .0306 16, 8 . 000 .78 .0019 -3.6 
Canard 
2 
. 0000 6 0 750 ,0478 15 . 7 .000 .77 . 0041 -5.4 
Interference 
2 
.0042 8 0 975 .0705 13 . 8 .000 ,77 .0069 -7 .1 
Wave .0000 10 0 1 148 .1903 6. 0 . 000 .33 .0087 -8.7 
External .OOOO 12 0 1 298 .2602 5 . 0 .000 .30 . 0134 -10. 4 
3 
Tanks 
2 
. OOOO 14 0 1 435 . 3412 4. 2 .OOO .28 .0197 -12 .2 
Bombs 
Stores 
Extra 
.0000 
.0000 
. OOOO 
Slope Factors 
Cl/Alpha (per radian) 
Cdl/Cl"2 
5.3743 
.1580 
Alpha Transition Zone 2-3 9.077 
Nov 18 96 
15:09:01 
Camber 
Cdmin 
Et 
.0000 
. 0156 
Programmed Flap Setting 
Flap Type Single 
C17-SHORT-ACSYNT-OUT 
0. 
519. sq. 
Detailed Aerodynamics Output 
Mach 
Altitude = 
Parasite Drag 
.80 
0. 
Induced Drag 
Friction 
Zone 
Body 
2 
.0112 
.0051 
Alpha 
.0 
CI 
ooo 
Cd 
.0168 
L/D 
.0 
Cm 
.000 
e 
.oc 
Cdtrim 
, oooo 
Deltrim 
.0 
Wing .0039 1 0 143 .0179 8.0 , 000 .80 .0002 -1.0 
Strakes 
2 
.0000 2 0 233 . 0212 13 .3 .000 .80 . 0006 -2 .0 
H. Tail .0014 3 0 419 .0265 15. 8 .000 . 80 .0013 -2.9 
V. Tail ,0008 4 0 551 .0337 16 .4 .000 ,79 . 0022 -3.9 
Canard .0000 6 0 804 .0530 15.2 . 000 .79 .0048 -5.7 
Interference .0041 8 0 1 042 .1337 7 . 8 .000 .41 .0077 -7.9 
Wave .0016 10 0 1 189 .2052 5.8 .000 .33 .0108 -9.2 
3 
External ,0000 12 0 1 342 .2793 4.8 .000 ,30 . 0163 -11.0 
Tanks .oooo 14 0 1 482 .3649 4.1 .000 .28 .0235 -12.8 
3 
Bombs 
Stores 
Extra 
Camber 
.oooo 
.0000 
. oooo 
Slope Factors 
Cl/Alpha (per radian) 
Cdl/Cl-^2 
Alpha Transition Zone 2-
Programmed Flap Setting 
3 
6.0661 
. 1585 
7.667 
0 . 
Cdmin .0168 Flap Type Single 519. sq 
. 90 
0, 
ft 
Mach 
Altitude = 
Parasite Drag 
Friction 
Zone 
Body 
2 
wing 
2 
Strakes 
2 
H. Tail 
2 
V. Tail 
2 
Canard 
2 
Interference 
4 
Wave 
4 
External 
4 
Tanks 
4 
Bombs 
Stores 
Extra 
Induced Drag 
0110 Alpha Cl Cd L/D Cm s Cdtrim Deltrl m 
0050 0 000 . 0852 0 .000 .00 ,0000 0 
0038 1 0 159 .0866 1 8 . 000 ,83 .0002 -1 1 
0000 2 0 315 . 0905 3 5 .000 .82 .0007 -2 1 
0013 3 0 465 .0969 4 . 8 .000 .82 ,0016 -3 1 
0008 4 0 612 .1054 in CO .000 .82 . 0027 -4 2 
0000 6 0 893 . 1285 6 . 9 .000 .81 .0058 -6. 2 
0023 8 0 i 082 .2440 4 . 4 .000 .33 . 0131 -9. 5 
0719 10 0 i 189 .3036 3 . 9 .000 .29 .0195 -11. 3 
0000 12 0 l 285 .3720 3 . 5 .ooc .25 . 0280 -13 . 3 
oooo 14 0 l 371 .4496 3 . 1 , 000 .23 .0396 -15. 5 oooo oooc Slope Factors Cl/Alpha (per radian) 
Cdl/Cl"2 
5.6120 
.1938 
Alpha Transition Zone 2-3 6 . 514 
C17-SH0RT-ACSYNT-0UT 
CDLLLLJKI .0000 
IDRNIN 
IT 
. Q852 
PROGRASONLFLD FL*P Setting 
FLAP TYPE SINGLE 
0. 
519, SQ. 
Output tor Module V 4 
1 BUG JUS SUMMARY 
SR = 6,21 FEET 
15.50 FEET 
= 4200. (.0 P<::JN"3 
5.90 
4 . 
3800.00 SQ FEET 
.EMT OF ENGINE CORKKLTF! A i RFLOW 
THRUST •- FJ«::HE THRUST [POUNDS PER ENGINE) 
SFC = EKGINE SPBC3KIC FUEL. CONSUMPT £C •'. 
THRUSTU- THRUST PER ENGINE IN LBS, W/O In.:-. Al, DRAG CORR 
SFCU = SFC.l/HR, W/O INSTALLATION DRAG CORft 
COINS = TOT INSTALLATION :>HA3 COEF PER A/C (JWIIIG REF) 
ENGINE DIAM 
ENGINE LENGM-. 
ENGINE HEIGHT 
HYPASS RATIO 
HO OF ENGIK-S 
DRAG REF AREA 
PWCC = PER1 
ALT 
.400 10000, 
.500 20000. 
PWCC THRUST TrIRUSTu SFC SFCU CDINS 
100 . 335". 33712. 404 .402 .003 1 
9;?. 3ZI72. 32320. 420 . 418 .002 5 
96 . 2 909V. 29232, 421 .419 .0024 
94 , 25361. 25484. 422 . 420 .D022 
9 2 , 21337. 21446. 434 .431 D019 
90 . 16654. 16717, 477 .474 .UUIV 
SA. 9877 . 9948 . 682 .677 .0013 
86 . 7781 . 7852 . 726 .720 . 0013 
94 . 6421 . 6494 . 727 , 719 .0013 
a.:. 5000 . 5073. 757 . 716 0 "••-•< EO. 3 417 . 3493 . 876 . B5R ,.!01I 78 . 1362 . HIS 1 679 1 .613 , 0D10 
100. 2 !H5 . 22251. 494 . 4B8 .0017 
98 , 20100. 20350. 498 . 492 .0016 
96 . I76E0. !7900. 498 .491 .0015 
94 . 15177, 15104. 505 .497 .0015 
92 . 12582. 12793, 527 : isle .0014 
90. 973 5. 992 8 . .572 .0012 
88. 6298. 6470 . 766 . 745 ,0011 
86. 5072 . 5246, 797 . 770 .0011 
84. 4094 . 4273 . 815 .781 .0012 
82 . 3077 . 325a. 878 . 833 .0012 
80 , 1983 . 2163 . 1 073 [JR5 . 00)2 
78 . 821 2 
4 i;., .00 30 100 . J 4G74. 1*320. 523 .515 ,0015 
98 . .3028. 13268. 520 . 0015 
°6 . 113 • . JI622. 522 .511 . 0014 9 4 . 5-737 9960 . 532 . 52D . 0014 12 . 6036 8248. 557 . 513 .OOU 90. 6218 . 6417 . 617 . 597 .0012 
8B , 4140 . 1321 795 .752 .0011 
96 . : 24 . 331. . aid .775 . 0( 2 
.650 30000. 
.750 40000. 
.800 50000. 
'A 2615. 2817 818 .791 .0012 1947 . 2112 .931 -917 .0012 80. 1200 . ,.393 1 191 1.025 .003 2 78 330, 507 3 
: • 2.111 .00 
100. 9500 . 9738 5 62 . 548 .0013 
98 . 8387. 8621 36: . 546 . 0013 
96. 7269 . 7L23 566 .549 . 5013 
94 6196 . 6426 580 .560 . 0013 
92 5091 . 5317 610 • -4 .0013 
,0. 3547 . 4166 674 .639 .0012 ? T: 2716 . 2 919 830 .77; .001] fl 5 . 2160 . 2379 874 . >'J3 , 0012 84 . It89 , 1910 920 .814 .001^ 
82 1210 . 143.-! 1 037 . 877 .0013 
80. 710 . 92H 1 391 1 . 064 .0012 
73 . 15b , 359 4 723 2 .080 .0011 
100 fi061 . 625'' 587 .569 .0013 
98 5330 . 5r- 539 , 56 8 .0014 
96 . , • L3 . 4B1C 597 . 572 ,0014 
34 . ,D' . 4110 614 .583 .0014 
92 . 3201 . 3402 647 .6 39 . 0D14 
90. 2482:. 2 679 714 . BL'2 .0013 
88 17?-* . 191 j 870 . 7P5 .0013 
86. 1358 , 156 3 926 . 804 ,0014 
B4 . 1012 , 1252 993 . 827 ,0014 
32 . 730 . 937 145 .891 . 0014 
80, 108 . 609 1 608 I 077 .0014 
78. B*. 250 7 569 i._!87 .0013 
100. 3823 . 3973 6!2 . 589 ,0011 
3356 . • 615 . 589 .0015 
96 . 2899 . 3055 625 . 593 ,0015 
2449 . 2607 644 .605 .0015 
92 . 2002 . 21(0 £31 . 631 .0015 
90. 15 50. 1706 753 . HA .001S 
n'i . :<<jTj. 1231 916 . i: 03 
.0015 
86, 842 . 1006 98J .822 . 0016 
84 . 636 . 807 1 072 . aig .0017 
82 437 . 606 1 2L,9 . 'JOB .0016 
80. 234 . 398 1 845 .0016 
7B. 23 . 173 14 JJ9 1 .887 .0015 
SEA-LEVEL STATIC THRUST = 40700. (MAX) 
SEA-LEVEL SFC = .3 28 
OUTPUT FOR MODULE # 1 
FUSELAAC DELLNIRI.N (TYPE 21 
NOSE LENGTH 23 . 060 
^OE5 Fineness Ratio . . 000 
Constant Section Length 61.005 
Afterbody Length 75.60
Afterbody Fineness Ratio 3.590 
OVERALL Lujiuth 160.67
KNXIMJRO DIAMETER 21.060 
BNDY plnnfnnn AREA 2956.015 
FUSW.AGF CROSS SECT UN 312 LHG TO ACCOMOrJATK PAYLOAD 
15:09:01 C17-SHORT-ACSYNT-OUt 
PAYLOAD WIDTH 
PAYLOAD HEIGHT 
THICKNESS OF WING ROOT 
MAX THICKNESS OF WING FOR FREE FIT 
DIAMETER REQUIRED FOR WIDTH OF EMBEDDED ENGINES.. 
DIAMETER REQUIRED FOR HEIGHT OF EMBEDDED ENGINES. 
. 00OOE+00 
. 0000E+OC 
1.771 
, O0OOE+00 
.O00OE+00 
. 00OOE + 0O 
DIAMETER REQUIRED TO ENCLOSE BOX 4.771 
REQUIRED DIAMETER..(MAX OF 3 ABOVE) 
RADIUS OF ENGINE POD 
ANGLE OF ENGINE PLACEMENT (ABOVE HORIZONTAL). 
STAND-OFF DISTANCE (NON-DIMENSIONAL) 
STAND-OFF DISTANCE (FT.) 
LOC. OF CENTER OF ENGINE 
4.771 
.975 
.2300 
.3010 
1 .196 
7.557 
AIRCRAFT INTERNAL ARRANGEMENT 
ITEM LENGTH INITIAL FINAL 
STATION STATION 
RADAR .000 .000 .000 
ENGINE 15.500 .000 15.500 
NOSE LENGTH 
AFTERBODY BEGINS AT 
OVERALL LENGTH 
MAX. AFT FUEL LOCATION 
DELTAX DUE TO PAYLOAD AFTERBODY MISMATCH. 
DELTAX DUE TO PAYLOAD-FUEL OVERLAP 
DELTAX DUE TO FINENESS RATIO REQ 
ACTUAL-REQUIRED CREW DIAMETER 
ACTUAL-REQUIRED PAYLOAD DIAMETER 16.29 
ACTUAL 
DIAM 
.000 
.000 
21.06 
85.06 
160.7 
122 .9 
1000 . 
1000. 
64 . 00 
21 .06 
REQD 
DIAM 
.000 
-138.246 
ACTUAL-REQUIRED POWER PLANT DIAMETER. 
WING ROOT THICKNESS IN BODY 
FUSELAGE WALL THICKNESS 
VOLUME OF FORWARD FUEL 
VOLUME OF REAR FUEL 
-10.94 
4 .771 
.OOOOE+00 
.0O0OE+O0 
, 0O0OE+00 
ACTUAL-REQUIRED FUEL VOLUME 2968 
Fuselage Definition Nacelle Definition Nacelle Location 
X R Area 
00 00 00 
1 05 1 64 10 61 
to 11 3 03 28 85 
3 16 4 03 50 92 
4 21 4 89 75 24 
5 26 5 66 100 80 
6 32 6 35 126 87 
7 37 6 98 152 87 
8 42 7 53 178 35 
9 48 6 04 202 92 
10 53 8 49 226 26 
11 58 8 89 248 09 
12 64 9 24 268 18 
13 69 9 55 286 34 
14 74 9 81 302 39 
15 80 10 03 316 20 
16 85 10 21 327 65 
17 90 10 35 336 65 
18 95 10 45 343 13 
20 01 10 51 347 04 
21 06 10 53 348 34 
27 46 10 53 348 34 
33 86 10 53 348 34 
40 26 10 53 348 34 
46 66 10 53 348 34 
53 06 10 53 348 34 
59 46 10 53 348 34 
65 86 10 53 348 34 
72 26 10 53 348 34 
78 66 10 53 348 34 
85 06 10 53 343 34 
B8 84 10 61 353 92 
92 63 10 66 356 83 
96 41 10 66 357 19 
100 19 10 63 354 81 
103 97 10 55 349 72 
107 75 10 43 341 96 
111 53 10 27 331 53 
115 31 10 07 318 49 
119 09 9 82 302 92 
122 87 9 52 2B4 92 
126 65 9 18 2 64 60 
130 43 8 78 242 12 
134 21 8 32 217 66 
137 99 7 81 191 4S 
141 77 7 22 163 76 
145 55 6 55 134 90 
149 33 5 79 105 27 
153 11 4 90 75 33 
156 89 3 81 45 54 
160 67 2 07 13 51 
x-xnose R Area X Y Z 
.00 3 97 49 .63 30 30 24.89 9 34 
7 .75 3 97 49.63 30 3C -24.89 9 34 
23 .25 3 97 49.63 43 48 48 .88 9 34 
31.00 3 97 49 . 63 43 48 -48.88 9 34 
Fuselage 
Max. Diameter 21.060 
Fineness Ratio 7,629 
Surface Area 9434.115 
Volume 45419.180 
Nacelles 
7.949 
774.161 (each) 
Nov 1$ 9ft 
15:09.01 C17-SHORT-ACSYNT-OUT 
Dimensions of Planar Surfaces (each] 
GEOMETRIC TOTAL VOLUME COEFF 
EFFECTIVE TOTAL VOLUME COEFF 
.745 
.745 
.075 
.075 
EXTENSIONS 
Centroid location at. 
Area . . 
Sweep Angle 
Wetted Area 
Volume 
Total Wing Area... 
Total Wetted Area. 
Strake 
.00 
.00 
. 00 
. 00 
.00 
3800.00 
22142.18 
.00 
. 00 
Tank 
Wing 
Fusttl 
Fus«2 
Total 
FUEL 3 
Volume 
5292. 
0. 
0. 
A N K S 
Weight 
264612. 
0 . 
0 , 
264612. 
Density 
50.00 
50.00 
50.00 
Mission Fuel Required = 116237. 
Available Fuel volume in Wing = 6615, 
Aircraft Weight = 497289.406 lbs. 
Aircraft Volume = 55156.949 cu.ft. 
Aircraft Density = 9.016 lbs./cu.ft. 
Output for Module (t 11 
*********************** ********* ******* 
Wing H. Tail V. Tail Canard Units 1 SUMMARY ACSYNT OUTPUT -- • NASA, AMES RESEARCH CENTER 
NUMBER OF SURFACES. 1 .0 1.0 1.0 1,0 + ENGLISH UNITS -
PLAN AREA 38 OO.O 8 45.0 BBS. a .0 [SQ.FT.) ***» MCDONNELL DOUGLAS C-17 TRANSPORT MISSION ***•« * 
SURFACE AREA 6779.8 1696.1 1135.6 .0 (SQ.FT.) + DISTANCES IN FEET 
VOLUME 7652.7 704 . 6 13 80.5 .0 (CU.FT.) 
SPAN 165 .409 65 ,000 26 . 173 .000 (FT. 1 + WEIGHTS IN LBS. 
L.E. SWEEP 28 ,418 30 .763 41 ,082 .000 (DEG.) GENERAL FUSELAGE WING HTAIL VTAIL 
C/4 SWEEP 25 .000 27 .000 41 .000 .000 (DEG.) + FORCES IN LBS. 
T.E. SWEEP 13 . 601 14 .165 40 .753 .000 [DEG.) 
ASPECT RATIO 7 ,200 5 .000 1 ,000 .000 + PRESSURES IN LBS/PT* *2 
ROOT CHORD 35 .344 18 .571 26 .304 .000 (FT. ) WG 4972 88. LENGTH 160 7 AREA 3800.0 845 ,0 685 .0 
ROOT THICKNESS 57 .257 20 .057 34 .721 ,000 (IN. ) W/S 130.9 DIAMETER 21 1 WETTED AREA 6779.8 1696.1 1135.6 
ROOT T/C .135 .090 , 110 ,000 T/W .33 VOLUME 45419 2 SPAN 16S.4 65.0 26.2 
TIP CHORD 10 . 603 7 .429 26 .041 .000 [FT. ) N(Z) ULT 9.0 WETTED AREA 9434. 1 L.E. SWEEP 28 . 4 30.8 41.1 
TIP THICKNESS 13 . 614 7 .131 34 .374 .ooo (IN. ) CREW 0. FINENESS RATIO 7 . 6 C/4 SWEEP 25.0 27 . 0 41.0 
TIP T/C . 107 ,080 .110 .000 PASENGERS 0, ASPECT RATIO 7.20 5.00 1.00 
TAPER RATIO .300 .400 . 990 .000 TAPER RATIO .30 .40 . 99 
MEAN AERO CHORD.... 25 .194 13 .796 26 . 173 .000 (FT. ) ENGINE WEIGHTS T/C ROOT .14 .09 .11 
T/C TIP .11 .08 . 11 
LE ROOT AT 37 .758 135 .071 113 . 640 .000 [FT . ) NUMBER 4. W WG ROOT CHORD 35.3 18.6 26.3 
C/4 ROOT AT 46 . 594 139 ,714 120 .216 ,000 !FT. ) LENGTH 15.5 STRUCT. 187373 . 37 . 7 TIP CHORD 10.6 7 .4 26.0 
TE ROOT AT 73 .102 153 .643 139 .944 .000 (FT. ) DIAM. 6.9 PROPUL. 21672 4 . 4 M.A. CHORD 25.2 13 .8 26.2 
LE M.A.C. AT 56 .118 143 .362 125 .029 .ooo (FT. ) WEIGHT 4200.0 FIX. EQ. 26641 5 . 4 LOC. OF L.E. 37.8 135.1 113 .6 
C/4 M.A.C. AT 62 .416 146 .811 131 . 572 . ooo (FT. 1 TSLS 40700. FUEL 116237 . 23 . 4 
TE M.A.C. AT 81 .311 157 .158 151 .202 .000 [FT. | SFCSLS .33 PAYLOAD 124000 . 24 . 9 
Y M.A.C. AT 33 . 930 13 ,929 13 .064 ,000 
LE TIP AT 82 .509 154 .416 136 .457 .ooo (FT. ) 
C/4 TIP AT 85 .160 156 .274 142 .967 .000 (FT. 1 MISSION SUMMARY 
TE TIP AT 93 .112 161 ,845 162 .498 .000 (FT. ) 
ELEVATION B .424 29 .499 9 . 477 .000 (FT. ) 
PHASE MACH ALT FUEL TIME DIST L/D THRUST SFC Q 
. 000 
.000 TAKEOFF .00 0 . 5353 . 6.0 5196.0 CLIMB ,46 10000. 2068 . 2.6 11 .8 16. 09 89426.6 .502 212 .0 
CLIMB .82 28000, 5023 . 8.6 63 .8 12 .08 48236.8 .648 325 .9 
CRUISE .75 28000. 75993. 259.0 1924.4 16 .44 25759.5 .654 271 .3 
Extension CLIMB .46 10000. 1588 . 2 ,0 9.0 16 .31 89426.6 .502 212 .0 
.00 CLIMB ,82 28000. 3431, 5.8 42 . 6 10.76 48236.8 .648 325 .9 
.00 CRUISE .75 28000. 16389. 60.3 448 .5 16.09 24308.4 . 664 271 .3 
LANDING 6201.2 
Block Time = 5.736 hr 
Block Range = 25O0.0 nm 
[without air and ground mariuever allowances) 
ICASE = 4 (Fineness Ratio Method) 
Nov 18 % 
15:08:57 C17-MIDDLE-ACS Y NT- IN 
= UATA BLOCK A 
**•* JiCSDMNELL 
S D^IA LLDCK a 
DOUGLAS C-17 TRAMSPORT HISSI 
S DATA BLOCK V 
END 
TRANSPORT 
5 3 5 
0.0001 
6 12 
7 2 6 
6 2 3 4 3 
TRANSPORT 
(4CDAC C-17 TRANSPORT * 
• • P = 0, NM 
SEND 
6 1.I2E+05 
MACH NO. ALTITUDE 
*£E START END STA7AT EJJL 
[JORIZONTAL 
DIST TIHE 
NO . 
TURN 
UIND 
"G-S 
=.FALSE. 
WKFJEL M IP IX 
570 585 1 
0.80 £50000 00 
3 i 0 0 0.00 0 .00 0 0 . 00 CL -U 0 50 0 CO 0 10000 O 0 1 D 0 .0 250. 0 i OOOO . 2 0 0 0 0 CLIMB 0 60 0 OO -1 29000 A 0 0 0 . 0 110. 0 i OOOO 1 2 -1 0 0 0 0 CRUISE 0 75 0 IS 28000 -i 3400 0 0 0 .0 0. N I OOOO I 4 0 0 C 0 0 CLIME 0 50 0 OU 0 10000 0 0 C 0 3 250. 0 i OOOO L 2 -1 0 0 
CL TIRO 0 60 0 OC -1 28000 0 0 1 .0 U .0 310 0 i OCCO 1 2 -1 0 0 „ 0 
CRUISE J 75 0 75 410=7 1 -1 300 0 0 . •' .I1 U. 0 i OOOO 4 0 0 A 0 0 
MCDAC C-17A TRANSPORT AERODYNAMICS MODULE 
SACHAR 
SOPTS AEOSB Z 0 220, ALMAX 20 000, AMC = 35 000, 
WG = 5S0000 000, IGRAPH 1, TjTJNOEE = 21 060, BTEF 1 OOO, RAL&iT 0 OOO, 
>.-• .:'.5.A ) 000, ROC 0 015, ROCM 0 020, 
SFIXW SFriF 1 OOO, S>! NDR = 0 860, MACHN - 0 750, 
WCREW = 1500 000, WCARGO - 112000.0, SPANAC C 000, SWPMAX 60 000. SWPM[N - 0 000, 
SEND XCDC 0 600, XCDW 0 600, AJCAN = 0, 
***** MCDONNET 
L DOUGLAS C-
17A TRANSPORT GEOMETRY ***** AT LL.I 3. IUORH 1, Ti ••• • IR = , 
SWING : ;J: :R = 0, ITRAP = 0, IXCD - 1, 
AR 7 AREA - 3AOO 000, DIHED -6 005, ELLlfC =F , Kl.LTPN =F , CLO - 0 OOO, 
LFLAPC 0 110, 3WBBF 25 000, TAPER 0 300, 0 000, 0 OOO, 0 OOO, 
TCROC'T 0 I 2 T, TCTIP 0. 107, TFLAPC 0.170, 0 OOO, 0 000, 0 
WFFRAC = 0 800, XWING 0. 290, ZROOT •= 0,800, 0 OOO, 0 000, 0 OOO, 
KSWEEP 1, CLOC = 0 OOO. 0 OOO. u 000, 
0 OOO. 0 OOO, ••: 000, 
5HTATL 0 000, 0 ooor 0 000, 
AR 5 000, AREA 845 000, CVHT 2 ooo, 0 OOO. PLOW O.OOO, 0 00 , 
SWEEP = 27 OOO, TAPER 0 400, TCSWOT 0*0, 0 000, 0 000 r 0 OOO, 
TCTrp = 0 OHO, XHTAIL -0 OIO, ZROOT = 1 765, 0 OOO, ( OOO. 0 ... , 
KSWEEP 1, 0 OOO, 0 000, CMO 0 000, 
SEND 0 OOO. 0 OOO. 0 000, 
SVTAIL 
AR 1 000, AF.FA 685 000, (*WT 0 100, 
0 
i: 
OOO, 
OOO, 
0 
0 
OOO, 
000, 
•:• 
0 
000, 
DOO, 
41 00Q, SWFACT i 000, TAPER 0 990, SMNSWP = 0 OOO. 0 OOO, 0 000, 
TCROOT = J 110, TCT TP 0 NO, VTNO I 000, 0 OOO. 0. OOO, 0 000, 
XVTAIL 0 871, YRDOT 0. 000, ZROO'I' ii S".'0. :• OOO, 0 OOO, 0 OOO, 
KSRFEEP 1. V OOO, YSWP 6 OOO, (; 000, 
SEND 0 OOO. 0 OOO, 0 OOO, 
SWPOD 0 OOO. 0 OOO, " OOO. 
DIAM = 10 000, LENGTH 10. 000, X -0 750, 0 OOO, 0 OOO, 
Y 0 301, Z 0, 230, SWFACT = 1 000, SEND 
. iD SAMULT 
SWPOD CSF = 1 OOO. ESSR i OOC. FCD 1 OOO. 
DIAM 10 000, LENGTH 10, 000, X = -1 000, FCDF - 1 OOO, 1-. -- I- ooo, FCDO = 1 OOO. 
Y 0 591, Z 0, 230, SWFACT 1 DOO, FCDW = 7 OOO, FCTJK6 = I OOO, FENG 1 000, 
SEND FINTF = 1 OOO, FLBCOR L OOO, FL.) = 1 OOO, 
5FUS FLECOR 1 000, FMDR = i. 010, FCDRA = 1 OOO. 
KDV.:\y, 21 OGO, BODL 160. 670, FRAR 3 590, 1 OOO, I OOO. : OOO. FRATIO 0 000, FRN t, 000, 1 000, I OOO, i AOO. JFJ7D 1 OOO, L OOO, i OOO. $ENGINE SEMD 
DIAM 8 000 , N - 4, CUTCOD 3, SATRIM 
CAND - 0 OOO. CFLAP 10. 0 10, CGM = O.S50, 
SSSSSSISSSSSSSSSSSSSSSSSSSSSSSSSSSSSSSSSSSSSSSSSSSJSSSSSSSSSSSSSSSSSSSSSSSSSSSS IT = 0 OOO. SPLAP 700 COO, SM - 0 OOO. 
STRT.ATA SPANF = 70 OOO. ZCG 0 OOC. IVCAM - 0 
CRMACK = 0 9^0, DELHP = 5000.00 - 0.200, ITRIM = i. 
DS51# 6 000, HMAKP = 5005 CJ.OOO, rii'llNP O.OOO. I, 1, I. 
QMAX BOO OOO, SM)'. ..• F : .100, SMMINP - O.2.Q0, I. 1, I, 
TIMTTJl 5 - 0, TIMT02 U.500, ULTI.F = 9.000, l. 1, I, 
BCOS*6P = 0 OIO. WFTRAP 300,000, WFUEL '720.000, SEND 
XDE3C = 8( OOO. I BUBO = O, :?LOT = 2, SAPET 
1F6IZE - 3, IPRINT - 0, IPSTOl 3 , IALP - 0, TAIIP = 3, 1COD l, 
LPSTQ2 v.vy.y :• - HMRROP * i, 1PLCT - 1, ••• 10, NMDTL = 6, 
HCRU3E 2, MLEGCL = 0, NLKGLO = 0, Al N - 0 OOO, I 000, 2 OOO, 
Nov 18 96 
15:08:57 
SEND 
SAD RAG 
ICDO 
SMTAMK 
SEN:.' 
SATAKE 
DELPTO 
LDLAND 
SEND 
3APRINT 
EOJOIN 
3 .000, 
? 000, 14.000, 
0.00D, 
o. ooo, 30000.oeu, 
o.DGO, o.ooa, 
o.ooa, 
0.400, 
TOO, 
700, 
900, 
0, 
0, 
0, 
0, 
0, 
0, 
0, 
0, 
0, 
0, 
0, 
o.ooa, 
o.ooo, 
o.ooo, 
0.00D, 
u ooo, 
Q.OOO, 
O.ooo, • no.-, o.ooo, o.ooo, 
o.ooo. o.ooo, 0.ooo, 
0,000, 
o.OOP, o.ooo, o.ono, o.ooo, 
o.ooo, o.oao, 
0.900, 
0.980, 
1.400, 
0,eoo, 
0.950, 
1.100, o.ooo, 
9.000, 
o.ooo, 
0.000, 
0.900, 
0.960, 
J.400, 
-1.000, 
29.000, 
-l.ooa, 
CDEKH 
CDTNK 
SHEXTR 
CLTO 
DEL LEI 
LDTO 
4.000, 
io.ooo, 
0,000, 
0.0D0, 
o .ooo, 
30000.000. 
o.ooo, 
o.ooo, 
o.ooo, 
0.500, 
0.800, 
o.fico, 
o, 
0. 
0, 
o, 
o, 
o, 
0, 
o, 
o. 
o.ooo, 
o.ooo, 
o.ooo, 
o.ooo, 0.ooo, 
o.ooo, o.ooo, 
0.000, 
o.ooo, 
o.ooo, 
o.000. 
o.ooo, o.ooo, 0.ooo, 
o.ooo, 
o.ooo, 
o.ooo, 
o.ooo, 
o.ooo, 
o.ooo. 
o,ooo
0.930, 
1.000, 
1,600, 
0. 900, 
0. 980, 
1.400, o.ooo, 
o.ooo, 
o,ooo, 
o. ooo, 
0.330, 
1.000, 
1.600, 
-1.000, 
30,000, 
-i.ooo, 
CLINPT 
CDONPT 
SMSTRS 
DELFLD 
JX-'LLTO 
C17-MIDDLE-ACS YNT-IN 
6 .000 
12.000, 
0.000, 
o,ooo, 
o.ooo, 
o.uoo, 
o.ooo. 
o.ooc, 
o. ooo, 
0.600, 
0.900, 
3 . 8 50, 
o, 0, 0, o, o, 
0, 0, 0, 
o, 
0, o.ooo, o. ooo, 
0.000, 
o.ooo, 
o.ooo, 
o. ooo, 
0,000, 
o.ooo, 
o.ooo, 
o. ooo, 0 , 000, 0.000, 
o.ooo, 
o. ooo, 
o.ooo, 
o .ooo, 
.000, 
.ooo. 
loo. 
loo, 
. 800, 
0.950, 
1 . 100, 
o.ooo, 
0.930, 
i.ooo, 
1 . too, 
D.000, 
0.000, 
o.ooo, 
0.800, 
0.950, 
1.100, 
45 . 000, 
io.ooo. 
= 0, IPCWJ = 0, IPEW3 
I PEST = 0, IPFliAP = 0, IPFRIC 
II7INTF • 0, 1FLIFT = 0, ] I'MIN 
[PlJAUE = 0, KSRHCR = 0, 
SEND 
" C-17 PROPULSION MODULE - USING CF6 ENGINE (CYCLE ANALYSIS) 
SLEWIS 
MWOAB : 
AESJDIA 
BA = 5 . 
SCFF 
YREN 
MODPRT 
ALTD 
XMACH 
SEND 
SAFTllEi 
SEND 
407OO.0. 
= 6.21, AENLE = 15.5, AENWT ^ 4?.00.0, 
9, 1P8 = ], SFALiP - 1,4, SFADSl' • .4 
= 1.350, WCWA1 - O.03O, 
95.000, EN - 4. 
= 1, NAB = 6, 
= 0.000, 10000.000, 
300OO.000, 40000.000, 
0.200, 0.400 
0.650, 0.750, 
KT5 = 0, 
SFBPP = 
XMDES 
XT7 
KODE - 2, 
1.4, ETAF1=0.90, 
1.400, 
0, 
6, 20000.000, 
50000.000, 
0.500, 
0.800, 
J 5:09:00 
ccccccc c 
c 
<-. c 
c 
OOOOOOO i'PFPPPP EEEEL.L.L 
O 
0 
D 
) 
r 
p p 
FFPFFPP 
F 
ccccccc ooooooo 
E.EEE 
E 
£ 
CONTROL V R O G R ;•, M 
FOR 
E N G I KEEP TNG SYNTHESIS 
TITLE 
MCDONNELL DOUGLAS C-1V THJUMSQiB1 MISSION 
] CARD IMAGES DF CONTROL OATA 
0 M 
1) $ DAT,". "LOCK A 
2) H0DOHN3LL DOUGLAS C-17 TRANSPORT MISSION 
3) .'- TATA BLOCK E 
4) 1 0- 0 O 
5) t DATA &LTJCK V 
6) EMU 
1 TETLKi 
• MClXJHiJl£«. DOU3LAS C-17 TRANSPORT M1S3JON *••«"« 
COHTfiflt, PARAMETERS; 
CALCULATION CONlftOL. NOAI.C -
KCnBER OF GLOBAL yESJO) VAEIAFLES, MDV = 0 
RFTMESFI of sensitivity variables, nsv =- O 
IH'JMBEH OF FUNCTIONS IN TOO-SPACE, NJVftR -
NUMBER OF APPROXIWiTlUa VAR, NXAPRX = 0 
INPUT INFORMATION MINT COOE, IPNFUT • G 
DEBUG PRINT CODE, IFDBG • 0 
CALCTJLATtOrt COMTPOL, NCALC 
VALUE 14EAK .HG 
C17-MTDDLE- ACS Y NT-OUT 
1 SINGLE ANALYSIS 
S 0JT1X12AT10W 
3 SENSITIVITY 
i TWO-VARIABLE FUNCTION SPA 
5 OPTIMUM SENSITIVITY 
S APPROXIMATE OmXIZATION 
KST1 HATED DATA SCCRAGE PEOtllKKMSPTTS 
INPUT 
9 
:ion 
9 
AVAILABLE 
5000 
IHTSGER 
EXECUTION 
1 
AVAILABLE 
1U00 
AAAAAAA ccccc:c sssssss Y Y N r: Twtr 
A A C 5 Y Y NN Li T 
A A C a Y Y N N [«. T 
AAAAAAA c sssssss Y N N K f 
A A S Y N ! . •: 
A A Y N H T 
A. A ccccccc Y N N 7 
NASA-AMES PROGRAM 
AIRCRAFT SYNTHESIS 
TITLE 
»*' MCPT-tONELL DOUGLAS C-17 TRANSPORT MISSION 
Ai;\:'' . . .-)•: - vk.-.n.-; 
1 Tl'J ; 
MCDOHMELL DOU3LAS C 1/ TP MiPO: 1' KISPTON 
AIRCRAFT TYPE - TRANS POP.'." 
CONTROL PARAMETERS: 
READ CONTROL, UREAL 
EKflCUTION CGMTKOL, MfiJEC 
WRITE CONTROL. MWkiTE 
NLTHBEK IDEMTlt-'YIMQ CONVEFGENCE 
VARIABLE FOR COMVESOEB VEHICLE, IOSJ 
MUWBEB IDENTIFYING COMPARISON 
VARIABLE FOH CONVERGED VEHICLE, JOBJ = 585 
570 
i 
Nov 18 96 
15:09:00 C17-MI DOLE-ACS YNT-OUT 
TAKEr.FF AND LANDING 
MODULES ARE CALLED FOR IHPUT IN THE FOLLOWING ORDER: 
6 12 3 4 
MODULES ARE CALLED FOR EXECUTION IN 
12 6 
E FOLLOWING ORDER: 
MODULES 
6 
ARE 
2 
W.LF.D FOR OUTPUT IN 
3 4 1 
Input for Module # 6 
1 initial WEIGHTS IWPUT pata 
ACSYNT MODULE NUMBER 6 
AIRCRAFT TYPE: TRANSPORT 
TITLE: **** MCCAC C-17 TRANSPORT * *' 
OCOHTRCL OF:IONS 
orjUKARY OUTPUT FHfNT CODE, IPSTJK = J OINTTTAL ESTIHATBS 
GLOBAL. ERROR PRINT CODE, K<il*&P •= 0 IT CODE « 
1, WEitJHT 13 FIXED 
GLOBAL COMMON IN ITIALI. ~. CODE, IN IT = 0 
DEBUG PRINT CODE, IPDBC, = 2 QUANTITY VALUE CODE QUANTITY VALUE COI 
GLOBAL PLOT CONTROL, IGPLT = 0 
DATA TRANSFER INFORMATION FILE, IRDDTfi 7 WAF 174000 0 WAIRC = seoo. c 
EATA THJ,N-;K:-:;, IN: DRMATION PRINT 
, IPDTR WAPU 232 . 0 WAMHOM = o. c 
WARM 0. 0 WBAG 17400. 0 
Wi XL = 
0 0 WBODY = 69600. 0 
WCAND n 
0 0 WCARGO = 1 12000. i 
VEHICLE CONVERGENCE INFORMATION WCREW = 
1 5 'J j . 1 WE 34800. 0 CONVEEtCENCE TOLERANCE, 'fOL = 1000DE-D3 WELT 5220 . WEP 2S00O. 0 ESTIM WCALC V£: WiJXT SLOPE = 8QQQQE+0C WETANK = 0 . 0 WFEQ i
 0 U . 
0 
BOUNDING WEIGH'!1, rfGMAX = 85O00E+06 NFS 4060. c WCA = 174Q. 0 
WGEAR -  . 0 HUDP 4640 . 0 
WHT 4640 . 0 WINST a 2900. 0 
WLG 29000. 0 SS = 0. 0 
WNA = 5400. 0 WPA 3,600 , 0 
MODULE IDENTIFICATION NUMBERS: WPASS = 8 , Q WPI, = 104100. c 
WPS 46400. 0 WSC 11600. 0 
NUMBER MODULE WTBUH = iflOOOO. C WVT SBD0. 0 
1 GEOMETRY WWIHll = 46100, 0 WBOMB = 0 . 0 
2 TRAJECTORY WENVP - 0 . 0 WPIV o. 0 
3 AERODYNAMICS WLlrTF - 0 . 0 WBB2 , 0 
4 PROPULSION wnipv = 0. 
5 STABILITY AND CONTROL 
6 WEIGSiTS 
8 SOMJC 3D0M 
9 ECONOMICS input Ear Module t 1 
1  SUMMARY OUTPUT 
******* '** • ** 
Geometry Input Data 
1 MCDONNELL DOUGLAS C-17 A TRANSPORT GEOKETHY *< 
IPRINT 
TDKLT 
Y.\ r.s 
KB 
FP. STRESS 
uj ::AB \ 
IMNTEN 
TECHI SLOPE!I) 
SLOPE|«1 
SLOPE US} 
1 IGRAF; 
0 IOBI.IL .00
 K2 .00
 K6 
.00 KP1 
.00 TEC11G 
30000. j .
 00 
0 
00 on oo oo 
.GEAR 
IMTGIl 
1 .00 
1 .00 
1 .00 
1. 00 
1 ITftlL = 
0 KHIHO = 
1.00 K3 
1.0C AFMACH = 
.00 KP2 
1 .00 WGTO 
DENS 
1 JFLTYP 
0 KHKKOR 
0 KBODY 
1.0 K4 
.85 MAX IT 
. 00 
5RO000. 
.100 F 
1 
0 
1 
1.0 
1 
.000 
1 .00 
!.. Do 
1.00 
1 .OO 
1 .00 
1 .00 
: .oo 
.00 
.00 
. CO 
oo oo on 00 00 
2 SWING 
3 AR 
4 LFLAPC 
5 TCROOT 
6 WF/'RAC 
7 KSWEEP 
8 SEND 
9 SHTAIL 
10 AR 
11 SWEEP 
12 TCTIP 
13 KSWEEF 14 S ZtfP 
15 SVTAIL 
16 AR 
17 svi. 
18 TCROOT 
7.200, AREA 
0.110, SWEEP 
0.135, TCTIP 
0.800, XWING 
= 3800.000, DIHED 
25.000, TAs-SR 
0.107, 1't'LAPC 
0.290, 2ROOT 
5.000, AREA 
27.000, TAPER 
0.080, XHTAIL 
1, 
1.000, AREA 
41.000, SHPACT 
0.110, TCTIF 
845.000, CVHT 
0.400, TCROOT 
-0.010, ZROOT 
685.000, CWT 
1.000, VAFKR 
0.110, VTNO 
-6.000, 
0.300, 
0.170, 
0. 800, 
1 .000, 
0.090, 
1.765, 
o.ioo, 
O.9B0, 
1 . 000, 
Nov IS 96 
15:09:00 CJ7-MIDD i-ACSYNT-OUT 
ID XVTA1L 
20 KSWEEP 
21 SEM 
22 SWPOD 
23 DIAM 
24 V 
25 SEND 
2 6 ."i':F0;: 
21 DIAM 
28 Y 
29 SEND 
30 SFUS 
31 BDMAX 
32 "PATIO 
33 SEND 
34 SHTFCIINE 
35 D'A.I 
36 SEND 
0.871, VFIOOT 0.000, EROOT 0 . 900 . 
10,000, LENGTH 
0,301, Z 
10.000, LENGTH 
0.591, Z 
21,060, BODL 
0.000, FKN 
8.000, N 
10.000, X 
0.230, SWFAC1 
LC.ONO, X 
0.230, SWFACT 
160,670, FRAB 
1.000, 
4, OU'I'COD 
-0,750, 
1.000, 
-1.000, 
1.000, 
3 .590, 
EN') OF ' METRY DATA CARDS 
36 LIKES READ 
QqcuiBtry Initial Output 
Fuselage Definition 
X R Area 
0U or 00 
1. 05 1 8-', 10 61 
U 3 03 2J! 35 
11 
4 03 SO -.. 
4 21 4 89 75 
5 2,; 1, 66 1O0 1 i 
6 32 6 35 12 6 £7 
1 37 f. 98 152 5 7 8 42 7 53 178 35 9 48 3 04 202 92 10 53 8 49 226 2FI 
11 5S SI 243 O'V 
12 6<- 9 2 . 268 : S 
.3. 69 9 ^5 286 34 
4 7 4 9 1 302 19 
^C IO 3 316 20 
.6 65 3 21 327 E 
17. >u JL 336 6 
95 10 15 343 
,*•> 
..3 Dl TO 51 347 
2; 06 10 53 318 . 1 
2 7 . 46 :O :3 *4H 3 4 
13 ,8« 
40.26 
46.66 
53.06 
• . 4. 
65. 86 
72.26 
7 
95.06 
38.84 
92.61 
98.41 
100.19 
103.97 
107.75 
ILL 
LIS: 
119 . f\" 
! 22 . B'7 
126,65 
11D.43 
134.21 
137.99 
141.77 
145.55 
149.33 
153.11 
56. B9 
: 60 . 67 
53 
IL 
10.53 
10.53 
10.53 
10-53 
10.53 
0.53 
. 0. R3 
10.53 
10.33 
10, 61 
10 . 69 
10.71 
10.59 
10. 63 
10.13 
10 .39 
0.20 
9 . 97 
9.69 
9.36 
8 . 97 
8.54 
8 . 03 
7 . 46 
6.81 
6. 07 
5.15 
4.12 
2 .40 
Max. Diameter . . 
Fineness Hntio. 
Surface AIM . . . 
Volume 
34FL .14 
348.34 
348.34 
318.34 
315.34 
149.34 
340 .14 
348.34 
346.34 
355.01 
359.07 
160.47 
359.18 
355.15 
348.40 
358.94 
326.65 
312.05 
294.77 
275,05 
253.04 
228 .89 
202.82 
175.05 
US .-86 
115.60 
4 . :>3 
53 .26 
18.10 
Fusol.ige 
21 .060 
7 . 629 
9511,863 
. . 45999.004 
G<?o-netry Initial Output 
DIMENSL_=:TJ OF PLANAR SURFACES (EACH) 
Wing H.Tall V.Tail Canard Units 
KL'KBER ,i SURFACES. ..0 1.0 1.0 
PLAN AREA 3800.0 845.0 685.0 
SURFACE AREA !.7 79.8 1696.1 113 5.6 
VOLUME 7652.7 704.6 1380.5 
SPAN 165.109 S5.000 26.173 
L.E. SWEEP 28.418 30.763 41.082 
C/4 SWF.EE 25.000 27,000 41.000 
T.E. SWEEP 13.601 14.165 40.7S3 
ASPECT RATIO 7.2 00 S.OOO I.OOO 
ROOT CHOKD 35 344 LA,571 26.304 
ROOT THICKNESS 57.257 20.057 34.721 
ROOT T/C .135 .090 . 110 
TIP CHCR1) 10.603 7.429 26.U41 
TTP THICKNESS 13.614 7.131 34.374 
TIP T/C , 107 .080 .110 
TAPES PATIO . 30D .400 .990 
MEAN AERO CHORD.... 25.194 13.796 26.173 
LE ROOT AT 37.758 195.071 113.640 
C/4 ROOT AT 46.594 139.714 120.216 
TE ROOT AT 73.102 153.643 139.944 
LE M.A.C AT 56.11B 143.362 125.029 
C/4 H.R C. AT 02.,;I6 146.811 131.572 
:N M.A.C AT 83.111 1ST.158 151.202 
I M.A.C AT 33,II, 13.929 13,061 
LE TIP AT 82.509 154.416 136.157 
1 . 0 
.0 (SQ.FT,) 
.0 |SQ.FT.) 
.0 (CU.FT.) 
.0 00 (FT.) 
.000 (DEG.) 
. 0BO (DEG.) 
.000 (DEG.) 
. 000 
.000 (FT.) 
.000 (IN.) 
.000 
.000 (FT.) 
.000 (IN.) 
.000 
.OOO 
.OOO (PT.) 
.000 (FT.) 
.000 (FT.) 
.000 (FT,) 
.' „ (FT.) 
.000 (FT.) 
.000 (FT.) 
.000 
.000 (FT.) 
Nov lit 96 
C/4 TIP AT, 
TE TIP AT.. 
ELEVATION.. 
85.160 156.274 142.967 
93.112 161.845 162.498 
8.424 29.499 9.477 
.000 (FT.) 
.000 (FT.) 
.000 (FT.) 
C17-MIDDLE-ACS YNT-OUT 
GEOMETRIC TOTAL VOLUME COEFF 
EFFECTIVE TOTAL VOLUME COEFF 
.745 
.745 
.075 .000 
.075 .000 
CRUISE .75 .75 41000 -1 500.0 .0 .0 .0 1.0000 1 4 0 0 0 0 0 
EXTENSIONS 
Strake Rear Extension 
Centroid location at. 
Area 
Sweep Angle 
Wetted Area 
Volume 
Total wing Area... 
Total Wetted Area. 
. 00 
.00 
.00 
.00 
.00 
3800.00 
22219.92 
.00 
. 00 
.00 
.00 
Input for Module # 3 
************************ 
FACTORS 
AERODYNAMIC IK7UT DATA 
MCDAC C-17A TRANSPORT AERODYNAMICS MODULE ** 
INTEGERS AND LOGICALS 
PAL EL = 1 ,ooc ALELJ - 3 NALF 10 ABOSB - 22C SHK 
FUEL TANKS 4 = 25 OOC 
Tank Volume Weight Density FBLNT = 010 IALF = 0 NMDTL = 6 ALMAX = 20 000 SM 
Wing 5292. 264612. 50.00 4 = 000 
Fusftl 0. 0 . 50.00 FCD = 1 .000 IALF 2 ECHOIN = 1 AMC 35 ooo SMNDR 
Fus#2 0 . 0 . 50.00 4 = 860 
Total 264612. 
4 
FCDF 
X = 60 000 
1 000 IAXE 0 ECHOOT = 0 BTEF = 1 ooo SWPMA 
Mission Fuel Required = 147001. FCDL = 1 ooo ICDO - 0 ELLIPC = F CGM 250 SWPMT 
Available Fuel Volume in Wing 6615. 4 N = 000 
FCDLH = 1 ooo ICOD = 1 ELLIPH = F CLLAND = -1 000 YO 
Aircraft Weight = 580000.000 lbs. 4 - ooo 
Aircraft Volume = 55736.773 cu.ft. FCDO = 1 000 I NORM 1 ELLIPW = F CLTO = -1 000 ZCG 
Aircraft Density = 7.344 lbs./cu.ft. 4 
FCDW 
ooo 
1 000 1NTM _ 0 CSF _ 1 ooo 
ICASE = 4 (Fineness Ratio Method} FCDWE = 1 ooo IPBLNT = 0 DELFLD = 45 000 
FCL = 1 ooo IPENG = 0 DELFTO - 25 ooo 
FCLH 1 ooo IPFRIC 0 DELLED = 30 000 
FDNOSE 1 ooo IPTEXT = 0 DELLTO = 10 000 
Input for Module # 2 FENG 1 ooc IPINTF = 0 ESSF = 1 000 
******* **«**************.*.», *************** ***** ******* * * ** * ** * * * FEXP = 780 IPLIFT = 0 EXA = 667 
TRAJECTORY INPUT FINTF 1 000 I PLOT = 1 EXC = 2 ooo 
FLBCOR = 1 ooo IPMIN 0 IT = 000 
FLD = 1 ooo IPWAVE = 0 LDLAND = -1 000 
TIMTOl = 5 . 5 MENDUR = 0. NCRUSE = 2 I PLOT = 2 FLECOR = 1 000 ISMNDR = 0 LDTO = -1. 000 
TIMTQ2 = .5 QMAX = 800. IPSIZE = -3 HMINP 0 FLNOSE 1 000 ISUPCR 0 MACHN = 75C 
FRFURE - .05 XDESC = 80.0 IPSTOl = 3 HMAXP - 50000 FLSCOR = 1 000 ITRAP 0 QH0Q1 - ooo 
DESLF = 6.00 WKFUEL = 1.000 IPST02 = 2 DELHP = 5000 . FMDR = 1 010 IVCAM 0 RCLMAX = 1 ooo 
ULTLF = 9 . 00 CRMACH = 990 IBREG = 0 SMMINP = .200 FSEP 1 000 IXCD 1 ROC 015 
RANGE = 1000. WKLAND = 570 IENDUR = 0 SMMAXP = 1.100 FTRIM = 1 000 KERROR 0 SFWF 1 . 000 
WFUEL = 182720. FLFAC = . 600 I PRINT = 0 DELMP = .200 
WFEXT = 0 . DECEL = . 250 KERROR = 2 WCOMBP = .01 
WFTRAP = 900. NLEGCL = 0 NLEGCR = 0 NLEGLO = 0 ARRAYS 
FWGMAX = 1.200 TOL = 001 MILCOM = 0 NMISS = 1 
NCODE = 0 ALIN = 000 1.000 2 .000 3 000 4.000 6. 000 8.000 IC .000 12 .ooc 
MMPROP = 1 4 14.000 
A LTV 0 . 0. 0. 0. 0. 0. 0. 0 . 30000. 
+ 30000. 
CDBMB .oooo .0000 .0000 .0000 .oooo .oooo ,0000 oooo oooo 
MISSION 1 4 .0000 
CDEXTR .0000 .0000 .oooo .oooo .oooo , oooo .oooo oooo oooo 
MACH NO. ALTITUDE HORIZONTAL wo, V1ND 4 .0000 
PHASE START END START END DIST TIME TURN "G"S WKFUEL M IP IX n B A P CDONPT = .0000 .0000 .oooo .0000 .0000 .0000 .0000 oooo oooc 
4 ,0000 
CLIME .50 .00 0 1000C .0 .0 . 0 250.0 1.0000 1 2 -1 0 0 0 0 CDSTR .oooo .oooo .0000 .0000 ,0000 .0000 .oooc oooo oooo 
CLIMB .60 .00 -1 28000 .0 .0 .0 310.0 1.0000 1 2 -1 0 0 0 0 4 .0000 
CRUISE .75 .75 28000 -1 3400.0 .0 .0 .0 1.0000 1 4 0 0 0 0 0 CDTNK = .oooo .0000 .oooo .0000 .0000 .0000 ,0000 oooo oooo 
CLIMB .50 .00 0 10000 .0 .0 . 0 250 .0 i.oooo 1 2 -1 0 0 0 0 4 .0000 
CLIMB .60 .00 -1 28000 .0 .0 ,0 310.0 1.0000 1 2 -1 0 0 0 0 CLINPT = 000 .000 .000 000 .000 .000 .000 ,000 .000 
C17-M1DDLE-ACSYNT-OUT 
.O0D 
CLO .000 
CLMIW = 
.000 
CM" . 900 
FCDRA -
J. -LOO 
FCLRA = 
. 000 
PLUM _.000 
FVCAM = 
1.000 
I5TR5 = 0 
ITS 0 
ITS 
0 
ITR1M • 
SMFXTR = 
] . .'".00 
.500 
SMJJWMB -¬ 
1 . 600 
.- ilNCDO = 
. ODO 
SMNSWP = 
.000 
SMSTRS = 
1 . 600 
SMTANK = 
. 000 
YSWP 
.000 
. 000 
. 000 
ooo 
1 .000 
1. 0D0 
i . c-oc 
I . ooo 
o 
o 
o 
i 
. 000 
.400 
.000 . ooo 
.ooo 
. ooo 
.ooo . ooo 
.ooo 
.000 
.ooc 
l. ooo 
1 .ooc 
i.ooo 1
 .000 
0 
o 
l 
.800 
.500 
.ooo 
.ooo 
.800 
.000 
. ooo 
.0.00 
. 000 
.000 
1 .000 
1.000 
1 .000 i.
 Q00 
0 
o 
o l 
. 900 
.600 
. ooo 
.000 
.900 
. 000 
. oou 
ooo 
.000 
.000 
1. 000 
i .ooo 
i. ooo 
1 .000 
0 
o 
0 
1 
.930 
.700 
.930 
.000 
,000 
.930 
. 0 rj g 
. ooo 
rny.ut TAR Module * 
PROPULSION INPUT 
VERSION 04-7 6 
,000 
. ODD 
1 .000 
1.000 
1.000 1
 .000 
c 
o 
o 
l 
. 950 
. 800 
. 350 , 000 
. 000 
.950 
.000 
,000 
.000 
.000 .000 
1 .000 
i. ooo 1,000 
1.000 
0 
0 
0 
1 
.980 
. 900 
. 960 
ooo 
.000 
. 980 
.000 
. 000 
.ooo 
.000 
i.ooo 
1,000 
i. oo-:. 
o 
c 
o 
i 
1. ooc 
.700 
i. ooo 
ooo 
.000 
i. ooc 
ooo 
.ooo 
000 
.000 
. ooo 
i .ooo i.ooo 
l. ooo 
I .ooo 0 
o 
0 1 
1.100 
. 800 
1. 100 
.000 
.ooo 
1. ] 00 
.000 
. 000 
-000 . ooo 
.ooo 
1. 00 
1. 000 i
 .ooo i
 .ooo 
0 
o 
o 
I 
1 .400 
. 850 
1 .400 
.ooo 
. ooo 
1.400 
.000 
. ooo 
SF5FC 
SMI 
CP. TWTC 
T51 VC1 
XMT 
FRPN 
1PR 
KEBHOR 
RT7 
NOZZ 
0{J (? SFSFC2 = 1
 .000 
SFSFC3 = i.ooo 
SODG = . TDSA = 
51B.000 >- • V 1N
 Ail 
0. TW3AB - 40700. 
500 T3 2800. T5H - 34O0 . 
0 . T7M 34 0. T71 = 0, 
9R0 WCTfAl = .030 XM02S 1 .400 
850 YREtJ 95. FRBT .000 
000 M = 1.150 P.LENG - 2.000 
1 IPRINT = 0 >T
 .PF\ 
_ 0 
0 RODE 2 KT5 - 0 
0 MINE'S F 0 NAB = 6 
0 NPHOP = 6 NSUMM 15 
IENG • 5 
THPiS VARIABLES ARE USED BY TABLE LOOK UP 
ESF = 1.000 NDTAII-, 6 IPDBUG = IIPRINT = 0 
ro = 
XT'. H = 
XMPRI * 
XPRI = 
MJPSlIl = 
,000 
Xl-'RIl = 
. 000 
XMPRI2 = 
.000 
XPRI2 = 
.000 
O. 
.200 
. OOO 
1 .000 
.000 
.000 
.000 
. 000 000 
. ODD 
.oo, 
.ooo 
10000. 
. 400 
.300 
1.000 
.ooo 
. ooo 
.000 
.ooo 
. CM 
.000 
. 000 
.000 
* * BEE • R 
200U0. 
. 5 00 
. 600 1
 . 000 
.000 
. 000 
.00;, 
.ooo 
30OO0. 
.650 
. 900 1.000 
. 000 
. 000 
.ooo 
4 0 0 0 0 . 
.700 
1 .200 
1 . 000 
.OOC 
.000 
.000 
.000 
(CF6 ) 
50000. .800 
4 . 000 
1 . 000 
.000 
.ooo 
.000 
, 000 
Vehicle Co.r/crgence *Y 
.5800OE+O6 Eaf.imntpd Gr< is Weight 
Calling Module I* 1 
Call.liy Modu". •• if 2 
IN CRUISE, PI 6, 
DRAG = .26433E+G5 
LEG 1, 
TN = 
TtWUST DOES NOT MATCH DRAG WITHIN 
.231SDE+05 
IN CRUISE, PHAiL 6, LEG 2, THRUST DOES NOT MATCH DRAG WITHIN 3 PERCENT 
• ' c- 17 PROP!.: S 1 ON MODULE USING CF6 ENGINE [CYCLE ANALYSIS) **•* DRAG => 260B9EH-05 TN = .233 1..E+05 
AllM ' A 6 210 AENLE 15 500 AENHT _ 4200 000 IN CRUISE, PHASE 6, LEG 3, THRUST DORS NOT MATCH 
ALT I = ooo AM = 000 ATUKB = 385 DRAG = .25753E+G5 TN = .2J1LOE+05 
AENTH 000 
AUAHNG Q D 0 AWAENG - 157 DA - 5 900 
D3LPR = ooo DE: J 1 = 100 000 DEPWCC 2 000 
IK CRUISE, PEiftSE 6, 
LEG 4, THRUST DOES NOT MATCH 
DIA1 CO 200 EAB1 = 75C EHA - 940 DRAG = .25425E+05 TN = .23110E+O5 
EDI 750 ETAC1 S20 ETAF1 9CC 
ETAT1 * 920 HTR = 300 HVF 18600 OOD Calling Module H 6 
MACU1 1 000 MACH2 1 100 PCUFAC * 1 OOU Calculated Gruyt Weight - .5719 h06 
POEA 7.3 «••• 3 PRFD 1 560 Pl-JCC - 100 000 
Slope of Wcalr vs. Went, line = .80000E+00 
P11PI = 1 720 P2771 = 30 000 R10A 1 ooo 
R32 = 940 R54 940 R54N Eatiroafed Gross Weighl: = .53949E+06 
R711 980 R V11N 7180 SCPR = 1 350 Calling Module * 1 
SFADP 1 400 SFADSP 1 SFAUXP = 1 000 Csil
 1 ing Module 1 SI DF.p = 1 000 SPfiPP 1 400 SfBTP - i 000 HI
 'VP 
* :. 000 SFINS? = 1 000 SFIP = 1 0DO IN CRUISE, PHASE 6, LEG 1, THIOST DOF.S NOT H\1C;£ 
.i3110E*0!b 
C17-MIDDLE-ACS YNT-OUT 
DRAG = ,I.4S»4EJ05 
Calling Module <t 6 
Calculated Cross Weight • . 551S2E-I OS 
Sltip-i of Wcalc vs. West line = .49321E+00 
Estimated Gro^s Weight = 
Calling Modulo t> 1 
Calling Module # 2 
. 5t40lE-<D6 
IN CRUISE, PHASE 6, LOG 1, THRUSr DOES MOT MATCH DRAG 
DRAG = .25337E*05 TN = .23110E+05 
IK IN 3 tERCEMT. 
IN CR 1-IASE 6, LKEJ 2, THRUST COBS NOT MATCH DRAG WITHIN 3 PERCENT. 
DSAG » .S5064E*05 TN = .231109*06 
IH CRUISE, PHASE 6, LEG 3, THRUST DOES NOT MATCH DRAG WITHIN 3 PERCENT. 
DRAG - .24751->05 TN = .23110EPOS 
IN Ci-.JIoE, .• -IASE 6, ISO 4, THRUST DOES NOT MATCH DRAG WITHIN 3 PERCENT. 
IN CRUISE, PEIASE £. LEG 4, THPUST DOES NOT MATCH DRAG WITHIN 3 PERCE* 
DRAG = .24388Et05 TM = .2311DE+05 
Calling Module # 6 
OUTPUT FAR MPRFULE 1 6 
Q:R.ax: 
resign LoaJ factor: 
'.litinute Lead Fiitov: 
Structure and Material: 
W±r>g Ecjuatinn: 
EI^y Equation: 
Weight Statement - Transpor'-
**** MCDAC C-17 TRANSPORT 
800. 
6 .00 •) .\i0 
ATuminuro. Ski.., Stringer 
Sanders Srnjfltion 
Sanders Equation 
DRA; = . ;-4444E+05 TW = . 23J.10E+05 Component Pounds Ki loo. rams PercenL S lopt, Fixec 
Calliny Module * o Airfra^IAJ Structure 200955 91153. 3 5 69 i<-
r^l-ruldted Gins; = Weigh: = .56355E+06 Wing 83026 39928. 1 7, n n 1 
OV/I: of WtalC ._. del 3in*> - .5010FIE+00 Fuse 1 • ge 6039/5 273=15 . 10 73 1 .00 1 CC Kj 
Horizons . Tail ( Low] 12 742 5780. 2 26 1 .00 1 00 Ho 
Estimated Gross Wei ght = .56309E+OS Vertical Tail 7781 J. . 1. 1 38 1 . ri0 1 00 No 
Calling Module » I NaceJ. e^ 6024 ;<732. 1 07 1 . 30 1 00 Mo 
Callin-j Module 1 2 Landing Gear 25937 11788. ( 1 . 00 1 00 No 
IN CRUISE, PHASE 6, LEG 1, THRUST DOES NOT MATCH DRAG WITHIN 3 PERCENT. Propulsion 21672 •W'l.'I . 3 85 No 
DRAG = .25327E+05 TN = .23110E+05 Engines ( 4) 19992 9068. 3 55 1 . 00 1 00 No 
Purl System 163(J 762 . 30 1 .00 1 00 No 
IN CRUISE, PHASE 6, LEG 2, THRUST DOES NOT MATCH DRAG WITHIN 3 PERCENT. Fixed Equipment 26909 12206. 4 78 1 00 No 
DRAG ^ . 25006KO5 TN = 
.23110ETOS 
Hyd £. Pneumatic 3379 1532 . 60 1 .oo No 
Electiicai 4000 1815. 7 3 1 .00 Nc 
Avioni cs 1899 861. 34 1 .00 No 
IN CRUISE, PHA.1!? 6, LEG 3, THRUST DOES NOT MATCH DRAG WITHIN 3 PERCENT. Instx_un,en' 'iii on 1078 489. 19 1 .oo NO 
l'J(/-.:: -- . 2469453+05 TN - ,23110E+05 De-ice & Air cond 0 0. 1 . 00 No 
Aux Power System 634 310 . .2 1 . 00 Nc 
Furnish t t-:c*pt 11345 5374. 2 10 1 .00 Ko 
IN CRUISE, PilASE 6, LEG 4, THRUST DOES NOT MATCH DRAG WITHIN 3 PERCKMT . Seats and Lavatories 0 0 . OO 1 .00 No 
DRAG * . 24388E' ..-3 TN = .2311OE+05 Ga]ley 0 0 . oo j .00 No 
Wise Cockpi t 0 0 . 00 1 . 00 No 
Calling Module # 6 Cabin F. Ting 6620 3003 . 1 18 1 .oc No 
Calculated Cross Weight = ,56311E*06 Cabin Emergency Equip 0 0 . 00 1 .00 NO 
Cargo Handling 5229 2372 . 93 1 . 00 HI' 
** End Vehicle Convergence ** Flight Controls 4021 1 824 . 71 1 .00 
3 Convergence It :- "HC ' L:LS 1 , • : Empty Weight 249536 113190. 44 Jl 
******** *****««•*» ******** **************** .... ******* * ***************** 
Calling Moduli.' 4 1 Operating Ittoms 0 0. 00 No 
Calling Module D 2 Flight Crew ( 0) 1500 680. 27 IT is; 
Crew fingg^ge and Provisions 100 45 . 02 J 
IN CRi;; EE, PRASE 6, liEG 1, THRUST DOR'S NOT MATCH DRAG WITHIN 3 PERCENT. Flight Ai 1-indent:s ( 0| 0 0 . 00 No 
DRAG = .25327E^5 -23llOE*05 Unusable Fuel and Oil 900 408 . 16 No 
P< jsrnger rvice 0 0 . oc No 
Cargo Containers 17920 8129 . 3 18 No 
IN CRUISE, PHASE 6, LEG 2, THRUST DOES NOT MATCH DRAG WITHIN 3 PERCE''.11 . 
DRAG • .2 50O6E+Q5 TN = .2311 i+U5 Operating weight Ejnp-.y 269956 122452. 47 94 
Fuel 181151 H2170. 12 n 
114 CRUISE, PHASE (-,, 
LEG i. i-HKUST DOES NOT MAT::H DRAG WITHIN 3 i>FRCEI4T. 
Nov 18 96 
15:09:00 C17-MTODLE-ACSYNT-OUT 
Payload 
Passengers 
aaggage 
Cargo 
Calculated Weight 
Estimated weight 
Percent Error 
( 0] 
112000. 
0. 
0. 
112000, 
50803. 19.89 
0. .00 
0. .00 
50803. 19.89 
563108. 255426. 100.00 
563086. 255416, 
.00 
No 
No 
No 
Yes 
No 
Output for Module # 2 
TRAJECTORY OUTPUT 
MISSION 1 (PAYLOAD = 112000. LB) 
PHASE M H CL ALPHA WFUEL TIME VEL 
SFC(I) THRUST(I: CD GAMMA W WA Q 
SPC(U) THRUST(U) CDINST L/D THR/THA PR X 
WARM-UP 0. 4902.8 5 .50 
.33 162800, 
TAKEOFF .27 0. 2 0300 12 ,00 450 .1 .50 296 . 
.42 131925. .4569 5 .07 557733.6 1418 . 87 104 . 
.42 131925. .0028 4 . 44 1 .00 1 .OC 6237 . 
2ND SEG .27 400. 2 0300 12 ,00 296 . 
.42 98944. 4569 8 .49 557733.6 1418 .87 104 . 
.42 131925. 002a 4 . 44 1 .00 1 .00 
CLIMB .46 10000. 6889 6 .13 2536.1 3 . 15 491. 
. 50 89427. 0441 5 .57 555197.5 1096 ,13 212. 
Cycle .49 90853. 0018 15 . 62 1. 00 1 .00 14 . 
CLIME .82 28000, 4363 3 .07 6824 ,9 11 .74 825 . 
.65 48237. 0348 , 53 548372.6 721 .40 326 . 
Cycle . 63 49995. 0014 12 .53 1.00 1 .00 88, 
CRUISE ,75 28000. 4190 3 .13 137476.1 443 .69 753. 
.65 26153. 0254 . 00 410896.5 587 .OC 271. 
Cycle .62 27559. 0014 16 .52 .54 1 .00 3297 . 
CLIMB .46 10000. 5053 4 . 40 1599.0 1 . 98 491. 
.50 89427. 0310 9 .05 409297.5 1096 .13 212, 
Cycle .49 90853. 0018 16 .31 1.00 1 .00 9 . 
CLIMB .82 28000. 3255 2 27 3459.1 5 . 82 82 5, 
.65 48237. 0302 1 . 53 405838.3 721 .40 326. 
Cycle ,63 49995. 0014 10 79 1.00 1 .00 43 . 
CRUISE .75 41000. 7032 5 40 15276.7 62 . 49 72 6. 
.59 23110. 0435 00 390561.7 354 ,58 148 . 
Cycle .57 23857. 0013 16 .17 . 80 1 .00 448 . 
LANDING ,23 0. 2 5956 12 00 257 . 
. 40 135854, 9733 19 77 459830.4 1404 .43 79 . 
.40 136803. 0032 2 . 67 1.00 1 .00 6588. 
Fuel Summary 
Total Fuel = 182051. 
Mission Fuel = 172525. 
Reserve Fuel = 862 6. 
Trapped Fuel = 900. 
Block Time 
Block Range 
Slock Fuel 
Takeoff Fuel: 
Warmup = 
Takeoff = 
4903 . 
450, 
Fuel Load: 
External = 0 
Internal = 182051 
8.914 hrs 
3900.0 n.m. 
172524.8 lb. 
Takeoff Field Length (total run) = 6237. ft 
Landing Field Length (total run) = 6588. ft Decel @ .250 Gs 
Nov 18 96 
15.09:00 C17-MIDDLE- ACS YNT-OUT 
Landing Field Length (ground run) = 3222 . ft 
Weight for Landing calculation = 459830. lbs 
Landing Thrust to Weight ratio = .295 
Takeoff Weight = 563086. lbs 
Landing Weight  390562. lbs 
Output for Module # 3 
Nov 18 96 
15:09:00 C17-MIDDLE-ACSYNT-OUT • 
Detailed Aerodynamics Output Camber .0000 
MACH 
Altitude 
. 85 
30000. 
Parasite Drag 
Takeoff Configuration: 
Induced Drag 
Flaps and Slats 
Friction 
Zone 
Body 
2 
.0111 
. 0050 
Alpha 
.0 
Cl 
784 
Cd 
.2249 
L/D 
3.5 
Cm 
.000 
e 
. 15 
Cdtrim 
.0050 
Deltriis 
-4,2 
Wing 
2 
.0038 1.0 934 .2418 3 9 .000 . 19 . 0067 -5 .1 
Strakes ,0000 2.0 1 078 , 2595 4 2 .000 . 23 .0087 -6.0 
H. Tail .0014 3.0 1 220 .2792 4 4 .000 ,28 . 0109 -6.9 
V. Tail 
2 
.0008 4.0 1 3 57 .3004 4 5 ,000 .31 .0132 -7.7 
Canard ,0000 6.0 1 621 ,3470 4 7 . 000 .38 ,0181 -9 . 4 
2 
Interference .0031 8.0 1 614 .3777 4 3 .000 ,34 .0137 -9.6 
Wave .0266 10 ,0 1 772 .4558 3 9 ,000 . 33 .0189 -11.1 
External ,0000 12 .0 1 705 ,4814 3 5 .000 .29 ,0262 -13.0 
1 
Tanks .0000 14.0 1 792 . 5702 3 1 .000 ,27 .0366 -15 .0 
4 
Bombs 
Stores 
Extra 
Camber 
.0000 
.0000 
. 0000 
.0000 
Cdmin 
ft 
.0407 
Slope Factors 
Cl/Alpha (per radian) 
Cdl/Cl~2 
Alpha Transition Zone 2-3 
Flap Setting 
Slat Setting 
Flap Type Single 
4 .1226 
. 1649 
7 .065 
25. 
10. 
519. sq. 
Mach = .90 
Altitude = 30000. 
Parasite Drag 
Landing Configuration: 
Induced Drag 
Flaps and Slats 
Friction 
ZONE 
Body 
2 
.0110 
.0050 
Alpha 
.0 1 
Cl 
293 
Cd 
. 6474 
L/D 
2.0 
Cm 
.000 
e 
.13 
Cdtrim 
.0130 
Deltrim 
-6.8 
Wing 
1 
.0038 1 0 1 456 .6788 2 1 .000 .16 ,0155 -7.6 
Strakes .0000 2 0 1 613 .7093 2 3 .OOC . 18 .0183 -8.4 
2 
H. Tail 
2 
.0013 3 0 1 767 .7411 2 4 ,000 .21 .0211 -9.2 
V, Tail . 0008 4 0 1 917 .7740 2 5 .000 .24 , 0241 -10.0 
Canard .OOOC 6 C 2 206 . 8428 2 6 . OOC .28 .0302 -11. 6 
Inter ference .0023 8 0 1 721 .5598 3 1 . 000 ,28 .0154 -10,0 
4 
Wave .0719 10 C 1 853 .6396 2 9 .OOC ,27 .0214 -11 .6 
External 
A 
,0000 12 0 1 972 .7289 2 7 . 000 .27 ,0293 -13 .4 
1 
Tanks . 0000 14 0 2 082 .8289 2 S .000 .26 .0400 -15 ,4 
4 
Bombs 
Stores 
Extra 
.0000 
.0000 
, 0000 
Slope Factors 
Cl/Alpha (per radian) 3.2262 
Cdl/Cl~2 .1716 
Alpha Transition 2one 2-3 6.514 
Cdmin 
ft 
.0852 
Flap Setting 
Slat Setting 
Flap Type Single 
45. 
30. 
519. 
Detailed Aerodynamics Output: 
C17-MIDDLE-ACS YNT-OUT 
Mach 
Altitude = 
Parasite Drag 
.40 
0. 
Induced Drag 
Friction 
Zone 
Body 
2 
.0118 
. 0053 
Alpha 
.0 
Cl 
. ooo 
Cd 
.0160 
L/D 
.0 
Cm 
.000 
e 
.00 
Cdtrim 
.0000 
Deltrim 
,0 
Wing .0041 1 0 .118 .0168 7 0 .000 .76 . 0001 - . 8 
4 
Strakes . oooo 2 .0 .233 .0192 12 1 .000 .75 .0004 -1.6 
H. Tail 
2 
,0014 3 0 ,345 .0230 15 0 . 000 .75 .0008 -2 . 4 
V. Tail .0009 4 .0 .454 . 02B2 16 1 .000 .75 . 0014 -3 .1 
4 
Canard .0000 6 0 665 .0424 15 7 .ooc . 74 .0030 -4.6 
Interference 
2 
, 0042 a 0 .867 .0611 14 2 . 000 .74 . 0052 -6.2 
Wave 
2 
.0000 10 0 I 060 .0840 12 6 .000 .73 .0077 -7 .7 
External . oooo 12 0 l 246 . 1107 11 4 .000 .72 .0107 -9.3 
4 
Tanks 2 .oooo 14 0 I 424 , 1410 10 1 .000 .72 .0140 -11.1 
Bombs 
Stores 
Extra 
Camber 
, oooo 
.oooo 
.0000 
.0000 
Slope Factors 
Cl/Alpha (per radianj 
Cdl/Cl-2 
Alpha Transition Zone 2-
Programmed Flap Setting 
5.8299 
.0616 
-3 16.894 
0 . 
Cdmin 
Et 
,0160 Flap Type Single 519. sq 
Mach = 
Altitude = 
. 50 
0. 
Parasite Drag 
Friction 
Kone 
Body 
2 
,0116 
.0053 
Induced 
Alpha 
.0 
Drag 
CI 
.ooc 
Cd 
.0159 
L/D 
.0 
Cm 
.000 
e 
. 00 
Cdtrim 
.0000 
Deltrim 
.0 
Wing 
2 
.0040 1 0 121 .0167 7. 3 ,000 .76 .0001 -.8 
Strakes 
2 
,0000 2 0 240 .0192 12 5 .ooo .76 .0004 -1.7 
H. Tail 
2 
.0014 3 0 355 .0232 15 3 ,000 .76 . 0009 -2.5 
v, Tail .0009 4 0 468 ,0287 16 3 .ooc .76 .0015 -3.3 
2 
Canard .oooo 6 0 685 .0436 15. 1 .ooo .75 .0033 -4.9 
Interference .0042 8 0 392 .0632 14. 1 ,000 .74 .0056 -6 .4 
4 
wave .0000 10 0 i 090 , 0872 12 . 5 .000 .74 .0084 -8.1 
External ,0000 12 0 i 280 .1150 11. 1 .000 .73 .0116 -9.8 
2 
Tanks .oooc 14 0 l 433 .3257 4 . i .000 .2S .0161 -11.8 
3 
Bombs 
Stores 
Extra 
.0000 
. 0000 
.oooc 
Slope Factors 
Cl/Alpha (per radian) 5.8634 
Cdl/Cl'2 .1509 
Alpha Transition Zone 2-3 13.323 
Cdmin 
ft 
. 0159 
Programmed Flap Setting 
Flap Type Single 
Camber .0000 
Nov iS 96 
15:09:00 C17-MIDDLE-ACS YNT-OUT 
Detailed Aerodynamics Output 
Mach = 
Altitude = 
Parasite Drag 
. 60 
0. 
Induced Drag 
Friction 
Zone 
Body 
2 
.0115 
. 0052 
Alpha 
. 0 
Cl 
ooo 
Cd 
.0158 
L/D 
.0 
Cm 
. 000 
e 
.00 
Cdtrim 
.0000 
Deltrim 
.0 
Wing .0040 1 0 126 ,0167 7 6 ,000 .77 . 0001 -.9 
Strakes 
2 
. 0000 2 0 250 .0193 12 9 . 000 ,77 .0004 -1.7 
H. Tail . 0014 3 0 370 .023 6 15 6 .000 .77 ,0010 -2.6 
4 
V. Tail .0009 4 0 4 87 .0295 16 5 .000 .76 .0017 -3.4 
Canard , 0000 6 0 712 .0453 15 7 ,ooo .76 .0036 -5.1 
Interference .0042 8 0 927 .0662 14 0 .ooo .75 . 0062 -6.8 
Wave .0000 10 0 1 132 . 0916 12 4 .000 .75 .0092 -8.5 
C 
External .0000 12 0 1 277 .2501 5 1 .000 .31 ,0125 -10.4 
Tanks .oooo 14 0 1 407 ,3249 4 3 .000 .28 . 0165 -11.7 
3 
Bombs 
Stores 
Extra 
Camber 
.0000 
, 0000 
.0000 
.0000 
Slope Factors 
Cl/Alpha (per radian) 
Cdl/Cl-2 
Alpha Transition Zone 2-3 
Programmed Flap Setting 
Cdmin 
ft 
Mach 
Altitude 
.0158 
,70 
0. 
Flap Type Single 
5.7573 
.1562 
10.880 
0 . 
519. sq. 
Parasite Drag Induced Drag 
Friction 
Zone 
Body 
t 
.0113 
.0052 
Alpha 
.0 
Cl 
ooo 
Cd 
. 0156 
L/D 
.0 
Cm 
.000 
e 
,00 
Cdtrim 
.0000 
Deltrim 
.0 
Wing .0039 1 0 133 ,0166 8 0 .000 .79 .0001 -.9 
2 
Strakes .0000 2 0 263 .0195 13 5 .000 .78 ,0005 -1.8 
2 
H. Tail .0014 3 0 390 .0242 16 1 .000 .78 .0011 -2.7 
V. Tail . 0009 4 0 513 .0306 16 8 .ooo ,78 . 0019 -3.6 
2 
Canard . oooo 6 0 750 .0478 15 7 .ooo .77 .0041 -5 .4 
Interference . 0042 a 0 975 .0705 13 8 .000 .77 ,0069 -7.1 
Wave .oooo 10 0 1 148 . 1903 6 0 .000 .33 .0087 -8.7 
j 
External .oooo 12 0 1 298 .2602 5 0 .000 .30 .0134 -10.4 
3 
Tanks .oooo 14 0 1 435 .3412 4 2 .000 .28 .0197 -12 .2 
3 
Bombs 
Stores 
Extra 
.0000 
. oooo 
.0000 
Slope Factors 
Cl/Alpha |per radian) 5.8743 
Cdl/Cl-2 .1580 
Alpha Transition Zone 2-3 9,077 
Camber .0000 
Cdmin 
ft 
.0156 
Programmed Flap Setting 
Flap Type Single 
0, 
519. sq. 
C17-MIDDLE-ACSYNT-0UT 
DETAILED AERODYNAMICS OUTPUT 
MACH = .80 
ALTITUDE = 0, 
PARASITE DRAG INDUCED DRAG 
FRICTION 
ZONE 
BODY 
.0112 
.0051 
ALPHA 
.0 
CL 
000 
CD 
.0168 
L/D 
.0 
CM 
.000 
E 
.00 
CDTRIM 
.0000 
DELTRIM 
,0 
WING .003 9 1 0 143 .0179 8 0 .000 .80 .0002 -1.0 
& 
STRAKES 
I 
.0000 2 0 283 .0212 13 3 .000 .80 .0006 -2.0 
H. TAIL .0014 3 0 419 .0265 15 8 .000 .80 .0013 -2.9 
2 
V. TAIL 
-5 
.0008 4 0 551 .0337 16 4 .000 .79 .0022 -3.9 
Z 
CANARD .0000 6 0 804 .0530 15 2 .000 .79 .0048 -5.7 
2 
INTERFERENCE .0041 8 0 1 042 .1337 7 8 .000 .41 .0077 -7.9 
3 
WAVE .0016 10 0 1 189 ,2052 5 8 .000 .33 .0108 -9,2 
J 
EXTERNAL .0000 12 0 1 342 .2793 4 8 .000 .30 .0163 -11 .0 
3 
TANKS .0000 14 0 1.482 .3649 4 1 .000 .28 .0235 -12.8 
3 
BOMBS 
STORES 
EXTRA 
CAMBER 
.0000 
.0000 
.0000 
.0000 
SLOPE FACTORS 
CL/ALPHA [PER RADIAN) 
CDL/CL"2 
ALPHA TRANSITION ZONE 2-
PROGRAMMED FLAP SETTING 
3 
6.0661 
.1585 
7.667 
0. 
CDMIN ,0168 FLAP TYPE SINGLE 519. SQ 
FT 
MACH 
ALTITUDE 
.90 
0. 
PARASITE DRAG INDUCED DRAG 
FRICTION 
ZONE 
BODY 
.0110 
.0050 
ALPHA 
.0 
CL 
.ooo 
CD 
.0852 
L/D 
.0 
CM 
,000 
E 
.00 
CDTRIM 
.0000 
DELTRIM 
.0 
WING 
•> 
.0038 1 0 . 159 .0866 1 8 .000 .83 .0002 -1.1 
Z 
STRAKES .0000 2 0 .315 .0905 3 5 .000 .82 .0007 -2.1 
H. TAIL ,0013 3 0 .465 .0969 4 8 .000 .82 ,0016 -3.1 
2 
V. TAIL .0008 4 0 .612 .1054 5 8 .000 .82 .0027 -4.2 
2 
CANARD 
2 
.0000 6 0 . 893 .1285 6 9 .000 .81 .0058 -6.2 
INTERFERENCE . 0023 8 0 1.082 .2440 4. 4 .000 .33 .0131 -9.5 
4 
WAVE .0719 10 0 1.189 .3036 3 9 ,000 .29 .0195 -11.3 
4 
EXTERNAL .0000 12 0 1.285 .3720 3 5 .000 .25 .0280 -13 .3 
4 
TANKS .0000 14 0 1.371 .4496 3 X .000 .23 ,0396 -15.5 
BOMBS 
STORES 
EXTRA 
,0000 
.0000 
.0000 
SLOPE FACTORS 
CL/ALPHA {PER RADIAN) 
CDL/CL-2 
5,6120 
.1938 
CAMBER .0000 
CDMIN 
FT 
.0352 
PROGRAMMED FLAP SETTING 
FLAP TYPE SINGLE 519. SQ. 
OUTPUT FOR MODULE # 4 
A****************************************** 
ENGINE SUMMARY 
************ 
ENGINE DIAMETER 
ENGINE LENGTH 
ENGINE WEIGHT 
BYPASS RATIO 
NO OF ENGINES 
DRAG REF AREA 
6.21 FEET 
15.50 FEET 
4200.00 POUNDS 
5.90 
4 . 
3800.00 SQ FEET 
PWCC = PERCENT OF ENGINE CORRECTED AIRFLOW 
THRUST = ENGINE THRUST (POUNDS PER ENGINE) 
SFC = ENGINE SPECIFIC FUEL CONSUMPTION 
THRUSTU= THRUST PER ENGINE IN LBS, W/0 INSTAL DRAG CORR 
SFCU = SFC, 1/HE, W/O INSTALLATION DRAG CORR 
CDINS = TOT INSTALLATION DRAG COEF PER A/C (SWING REF) 
MACH 
.200 
ALT 
0. 
.400 10000. 
.500 20000. 
ALPHA TRANSITION ZONE 2-3 6.514 
PWCC THRUST THRUSTU SFC SFCU CD IMS 
100. 33535. 33712, .404 .402 .0031 
98. 32172. 32320. .420 .418 .0026 
96 . 29097, 29232. .421 .419 .0024 
94. 25361. 25484. .422 .420 .0022 
92. 21337. 21446. .434 .431 .0019 
90. 16654. 16747. .477 .474 .0017 
88. 9877. 9948. .682 .677 .0013 
86. 7781. 7852. .726 .720 .0013 
84 . 6421. 6494 . ,727 .719 .0013 
82. 5000. 5073. .757 .746 .0013 
80. 3417 . 3488. .876 .858 .0013 
78. 1362. 1418 . 1.679 1.613 .0010 
100. 21985. 22251. .494 .488 . 0017 
98. 20100. 20350. .498 .492 .0016 
96 . 17660. 17900. .498 .491 .0015 
94. 15177. 15404. .505 .497 .0015 
92. 12582. 12793. .527 .518 .0014 
90. 3735. 9928 . .584 .572 .0012 
88. 629S. 6470. .766 .745 .0011 
86, 5072. 5246. .797 .770 .0011 
84. 4094. 4273. .815 ,781 . 0012 
82. 3077. 3258. .878 .829 .0012 
80 . 1983. 2163. 1.075 .985 .0012 
78. 665 , 825. 2 .440 1.969 .0010 
100. 14674, 14920 . . 523 , 515 .0015 
98. 13028. 13268. .520 .511 .0015 
96 . 11388. 11622. .522 .511 .0014 
94. 9737 . 9960. .532 .520 .0014 
92 . 8036. 8248 . .557 .543 .0013 
90. 6218. 6417 . .617 .597 .0012 
88. 4140. 4324 . .785 .752 .0011 
86. 3324 . 3511. .819 .775 .0012 
d 2645. 2837. .tit 791 .0013 1947. / . ' .932 B47 .0012 0. 1200 . .393 . 1.131 1 02 5 .0012 b . 
330. 507 . 3 .284 2 141 .0011 
.650 30000. 100 . 9500. 9738 . . 562 548 .0013 
98, 8387 . 8 62 4 . .561 546 .0013 
96 . :-. 3 3. 752 3 . . 566 549 .0013 
94 . 6196 , 6426 . . 580 560 . 0013 
92 . 5091. 5317 . . 6J0 584 .003 3 
• 0. 3947 . 4lfiG. . 674 fiJ9 .0012 i- : 
2716 . 2919 . ,830 7 73 . 0011 
1 . 2160. 2379 . . 974 793 .0012 
84 . 1689. 1910 . .920 R14 .0012 
82 . 1210 . 1432 . 1 .037 »"J7 . 0013 
80. 710 . 928 . 1.391 1 064 2 
78 . 53 . 359 . 4 .723 2 080 .0011 
750 40000. 100 . SQ61 . 5Z57 . . 587 5 0 9 .0013 
t 8 , 
5 JO. .. (0. .539 368 .0014 96 . 4613 . 4816. .597 572 . 0014 94 . 3906 . 4110. . 614 583 .0014 
92 . 3201. 3402 . . 647 609 .0014 90. 2433 . 2679 . .714 662 .0013 BP . 1727 . 1915 . .8 0 785 .0013 B6. 
I -.) r> . i 55-i , . 926 •o .0014 bi. 104 2 . 1252 . .993 827 .0014 82 . 730 . S37 . 1 . 14 5 891 ,00! 4 
30 . 408 . 609 . 1 . 6D8 1 077 .0014 
78 . 66 . 250 . 7 . 5b9 i 9S7 .5013 
.800 50000. 100 . 3823 . 3973. . r.i.2. 539 . Ml 1 
9£. 3356 . 3510. 
.6^5 
.0-J15 
16 . 2899. 3055 . . 625 5 9 3 • WIS 94 . 2449 . 2 60/. . 644 b05 .0015 92 . SOC-2 . 2160 . .681 631 .001! 90 . 1550 . 1706. .7" 1 684 -00.15 
88 . 1079 . 1231 . .916 803 . 0015 
86. 812. 1006 . . 9 83 823 .0016 
84 . 638. 807 . 1 . 072 844 .0017 
82 , 437 . 606. 1 .25? 9C3 .0016 
80 . 23 4 . 398. 1. 845 1. 086 .0016 
78 . 23 . 15
 5 . 
14.339 1. 887 .0015 
SEA-LEVEL STATIC H"sT'i (ST = 40700. [MAX)  SFC .328 
Output tor Module ft 1 ....... 
Fuselage Definition (Type 2) 
Nos^ Length 
Nose Fiii.rLLt.-orj Kjtio. 1 
Constant Sec: J:I i.ingth 64 
Afterbody |Hen3th 75 
Afterbody Fineness Ratio 3 
Overall Length ISO 
MaXirtrun Diameter 21 
Body PlahlDrrn Area 2556 
21.060 
000 
005 
605 
... > 
670 
060 
015 
C17-MIDDLE-ACS YNT-0 UT 
PAYLOAD NIHTH 
PAYLOAD HEIGHT 
THICKNESS OF WNG ROOT 
MAX THICKNESS OF VJ11MG FOR FREE FIT 
DIAMETER REO'JIRED FOR WIDTH. OF EMBEDDED F.NGTNISS . . 
DIAMETER HEOUIRED FOR HEIGHT OF EKBEEEED ENGINES. 
DJAMETER REQUIRED TO ENCLOSE BOX 
HEQUTSED CIAME.ER. . (MAX OF 3 ABOVE) 
RADIUS OF ENGINE POD 
AMOLE OF ENGINE PLACEMENT I ABOVE HORIZONTAL) 
STAND-OFF DISTANCE (NON-UJWENSIONALI 
STAMB-OFF DISTANCE (FT.) 
LOC. OF CENTER CF EWGi[Hii 
.OO00E-0D 
.00ODE*00 
4.771 
.O0ODE*Q0 
,OODOE+Ofl .OOOOEi 00 
4.77 .1 
4.77 1 
3.975 
.2JD0 
. .3010 
. i, is'* 
. 7.557 
13 
ATRCSAFT INTERNAL AH>"AJ"*J.ENENT ITEM LENGTH INITIAL STATION 
RADAR .000 .000 ENGINE
 15.500 .000 
FINAL STATION 
.000 
15.500 
NOSE LENGTH 
AFTEKSDDY BEGINS AT 
OVERALL T.KNGTH 
MAX. AFT FUEL LOCATION 
DELTAX CUE TO PAYLOAD AFTERBODY MISMATCH. 
DFLTAX L70E TO PAYLOAD-FUEL OVUF.LAP 
DSCLTAX DUE TO FINENESS RATIO REQ 
ACTUAL - R &3U I RED CREW J1AKFTFR 
ACTUAL - P EOO IREIJ PAYLOAD r rAMETEK 
ACTUAL-KEQOIPED POWER Prj.NT DIAMETER 
WING ROOT THICKNESS IN BODY 
FUSE:_AGK WALL THICKNESS 
VOLUME OF FORWARD FL:EL 
VOLUME OF REAR FUEL ACTUAL-Hr-.
 • i! RED FUEL VOLUME 
ACTUAL 
DIAM 
. 030 
.000 
21 .OS 
4S.06 
150.7 
122 .9 
64 . 00 
2.1 .06 
1G .29 
-1( 94 
4,771 .UUOOE+00 
.ooaiiKtoo 
.0OO0E+00 
1651 . 
REQD 
DIAM 
. COO 
10.597 
.-•Ij:'.l-:.,AGE CROSS SECTION SIZING TO ACCOMODATE PAYLOAD 
Nov 18 96 
15:09:00 
r U 3 e Del init} CON 
X R Area 
00 no ( 
i. 05 1 • i 7 3 ( . 3 3 7 3 JB1BS 3 16 4 "3 50 %Z 
A <:1 4 •9 75 24 a 
26 5 TOO.ao 
6 32 6 35 126 <• 
7 37 r ?S lb 2 17 
8 42 7 53 17A, 
9 48 8 04 202 J2 
10 Si 8 49 226 26 
11 58 8 89 248 09 
12 64 9 24 268 iij 
13 69 9 55 266 34 
14 74 9 s: 302 39 
13 50 10 03 31fi 20 
it 85 10 21 327 65 
17 90 3 0 35 336 65 
18 95 10 45 343 13 
20 01 10 51 347 04 
21 06 10 53 348 & 
2 7 46 10 53 348 34 31 86 10. 53 348 34 47 24 10.53 3iB 34 
46 66 10 53 716 '4 
S3 06 10. 53 348 J4 
49 46 10 53 348 34 
t'5 86 10 57 34S 34 
7/a 26 10. 5 1 348 34 
78 66 10 53 348 34 
8* 06 10 53 348 34 
Bfl 84 10 61 353 92 
92 6 3 10. < 356 88 
96 A ! 10 oO 357 19 
10'. : 7 JO < • 354 81 
101 77 10 . 55 349 72 
507 75 io. 43 34 7 96 
111 57 10 27 31
 L 
53 
IIS 31 10. 07 318 49 
1 19 c • 9 . 82 302 9 2 
132 ! 9 52 2 ti 1 j 
126 44 9 •j R 2 R SO 
130 4.-. S. 7E 242 ^2 
1J4 2 ! 8 . 32 217 66 
] 17 57 n 81 131 45 
141 7 7 7 . 22 1 6 } 76 
145 5 6 . 5C 134 90 
149 33 5 79 109 27 
15J 1 1 4 . 9,7 7^ 3 3 
156 S9 81 45 54 
ISO 
6 7 2 . 07 13 Si 
C17-MI DOLE-ACS YNT-OUT 
NACELLE EEFINIRIRN Mnzeille Location 
X-Xnose R Area X Y 7 
.00 7 .97 49.63 30 30 24 9 "'4 
7.75 7
 .97 
49 . 63 30 -2 4 3 ... 34 
23 .25 J .97 49 . 63 43 4 48 p- 9 34 
31 .OC 3 . 97 49.63 4l i -48 B( 9 34 
Max. Diameter 21.06 3 
Finenea* Kstio 7.329 
Surface Aiea S434.ll*; 
Volume 454 n . 780 
Nacelles 
7.949 
774.161 (each) 
Dinensicns oil: Planar Surfac»s (each) 
wing H.Tail 
NUMBER Of SURFACES. i.0 
PLAN AREA 3800. 0 
SURFACE A37.EA 6779.8 
VOLUME 7652.7 
SPAN 165.409 
L.E. SWEEP 2 9.416 
C/4 SWEEP 25.000 
T.E. S !P 13.6 01 
AfFfiCT RATIO 7.200 
ROOT CHORD 3 5.344 
ROOT THICKNESS 57.257 
ROOT T/C .135 
TIP CHSttB 10.603 
TIP THICKNESS 13.614 
TIP T/C . 107 
TAPER RATIO .3 00 
WEAN" AERO CHORD. ... 25. 194 
LE ROOT AT 37.758 
C/4 ROOT AT 46 . b94 
TE ROOT AT 73 . 102 
LE M.A.C. AT 58.11* 
C/4 M.A.C. AT 62.416 
TE M.A.C. AT 81.311 
Y V A . C . AT 33 . 930 
LE n P AT 82 .509 
C74 TIP AT 5 . 160 
Tl TIP AT SJ . 112 
ELEVA'.-H 6.424 
SIGMBUUC TOTAL VOLUME CCEFi' 
EFFECT!up TOTAL VOLUME COSFF 
1.0 
845.0 
"90.1 
/04 . 6 
65.000 
30.763 
27.000 
14.165 
5 . 000 
18.571 20.077 
.090 
7.429 
7.131 
.080 
.400 
13.796 
135.071 
139.714 
153.643 
143.162 
146.811 
157.158 
13.929 
154 .41-7 
156.274 
161.845 
29.499 
.745 
.745 
: .0 
685.0 
1135.6 
13H0.5 
26.173 
41.082 
41.000 
40,753 
1.000 
26.304 
34.721 
. 110 
2S.041 
34.374 
.110 
. 990 
26.173 
113 . 640 
120.216 
139.944 
121.029 
131,572 
151.202 
13.0E4 
] 6.457 
142.967 
162.498 
9 .477 
.075 
.075 
Canard Units 
1.0 
.0 (SQ.FT.) 
.0 (SQ.FT.1 
.7 (CU.FT.) 
.000 (FT.) 
.OD0 (DEG.) 
.000 (DEG.) 
,000 (DEG) 
. 0OD 
. OOO (I-'T . ) 
,050- (IN.) 
. 000 
.000 (FT.) 
.000 (IN.) 
.000 
, 000 .ooo 
(FT. ] 
.000 (FT.) 
.000 (FT.) 
.000 (FT.) 
.000 (ET.) 
.000 (FT,) 
.000 
,000 
.000 
(FT. ) 
(ST. .000 (FT .000 jFT .07! 
.000 
.000 
) 
(FT. ) 
(FT . ) 
fiXTENSIONS 
Strake 
Centroid location at...... . .00 
Area .0
SWRI=P Any i. e .0
Wetted Area 0 
Volume .0
Total Wing Area 3 800.00 
Total WETTED Area 22142.18 
Rear Extension 
.00 
.00 
.00 
, 00 
Tank 
Wing 
:•. • L 
SUA ! 
TOW I 
FUEL 
Vol* ,7e 
5292 
0 
•'i 
T A M K S 
Weiflhc 
264612. 
0 . 
0 , 
264612. 
Mission Fuel Re<juir*d -
Available Fuel VO±IJJIIC± In Wing 
Den¥ity 
50.00 
50.00 
50.00 
182057. 
6615. 
Aircr.-ft Wei^nt 
AircraCt VsLyrme 
iircraft Density 
563086.438 lbs. 
55156.949 cu.ft. 
10.209 lbs./cu.ft. 
I CASE = 4 (Fineness Ratio Mcrhiidl 
Nov IS 96 
15:09:00 C17-MIDDLE-ACS YNT-OUT 
Output for Module » 11 
*-**•*» ******************* 
SUMMARY ACSYNT OUTPUT -- NASA, AMES RESEARCH CENTER 
ENGLISH UNITS -
** MCDONNELL DOUGLAS C-17 TRANSPORT MISSION 
DISTANCES IN FEET 
WEIGHTS IN LBS. 
GENERAL FUSELAGE 
FORCES IN LBS. 
PRESSURES IN LBS/FT* 
WG 563108. 
W/S 148.2 
T/W .29 
N|2) ULT 9,0 
CREW 0. 
PASENGERS 0. 
ENGINE 
LENGTH 160 
DIAMETER 21 
VOLUME 45419 
WETTED AREA 9434 
FINENESS RATIO 7 
HTAIL VTAIL 
3800.0 845.0 685.0 AREA 
WETTED AREA 6779.8 1696.1 1135.6 
NUMBER i . W WG 
LENGTH 15.5 STRUCT. 200955. 35 .7 
DIAM. 6.9 PROPUL. 21672. 3.8 
WEIGHT 4200,0 FIX. EQ 26909. 4.8 
TSLS 40700. FUEL 182051, 32 .3 
SFCSLS . 33 PAYLOAD 112000. 19.9 
SPAN 
L.E. SWEEP 
C/4 SWEEP 
ASPECT RATIO 
TAPER RATIO 
T/C ROOT 
T/C TIP 
ROOT CHORD 
TIP CHORD 
M.A, CHORD 
LOC. OF L.E. 
165.4 
28.4 
25 .0 
7 . 20 
.30 
, 14 
.11 
35 .3 
10.6 
25 .2 
65.0 
30.8 
27 . 0 
5.00 
.40 
, 09 
.08 
18.6 
7.4 
13 .8 
26.2 
41.1 
41.0 
1.0C 
,99 
.11 
.11 
26.3 
26.0 
26.2 
37.8 135.1 113.6 
MISSION SUMMARY 
PHASE MACH ALT FUEL TIME DIST L/D THRUST SFC Q 
TAKEOFF .00 0. 5353 . 6.0 6236 6 
CLIMB .46 10000. 2536. 3.1 14 5 15 . 62 89426.6 .502 212 0 
CLIMB .82 28000. 6825. 11 .7 88 3 12.53 48236.8 , 648 325 9 
CRUISE ,75 28000. 137476. 143.7 3297 2 16.52 26152.9 . 651 271 3 
CLIMB .46 10000. 1599 . 2.0 9 0 16 .31 89426.6 .502 212 0 
CLIMB .82 2 8000. 3459 . 5.8 42 9 10,79 48236.8 , 648 325 9 
CRUISE ,75 41000. 15277. 62 .5 448 1 16.17 23109.9 .587 147 6 
LANDING 6587 8 
Block Time = 3,914 hr (without air and ground manuever allowances) 
Block Range - 3900.0 ran 
Nov 18 96 
TRANSPORT 5 3 5 570 5B5 10 0 7 0 7 0 o.oooi 0 .80 850000.00 0.00 
i . 00 o.oo 6 1 
2 3 4 1 2 6 6 2 3 4 1 
r:"AKSPC!K';' ''"• MCDAC C- 1 TRANSPUT ****** sosrs 
WGTO '480000 000, IGRAPH 1, 
SEND 
SPIXW 
WCKEW 1500 000, WCARGO = 50000.0, 
SENL 
MCDONNELL DOUGLAS C-17A TRANSPORT GEOMETRY ***** SWING 
Ai 7 200, AREA = 3800 ooo, B A -6 ooo, I.FLAPC 0. 110, £ :• ' 25 000, TAPER O 30D, TirROOT = 0 135, TCTIP 0 107, 7/FLAPC = 0 1FT. 
WFTBAC - 0 800, XWIHG 0 iSO, ZROOT - 0 BOO, 
K5WEEP 1, 
SEMIS 
SlITAlL 
AS = 5 ]QD, AREA 345 000, CVHT = l.ooo, 
SwEfcP - 2 000, TAPER 0 400, TCROOT 0 090, 
TCTIP 0 t>8t>, XHTML -0 030, ZROOT 1 765, 
Ksr-- 1 , SEND SVTATL 
AR = ' QDO, AREA 685 •' , CWT 0 100, 
SWEEP 4 000, SWFACT 1 ooo, TAPER 1} 990, 
TCROOT = 0. 110, TCTIP - n 110, VTNO = 1 000, 
XVTAIL = 0 871, YROOT ooo, ZROOT 0 900, 
MSWEEP 1, 
SFND 
SWPOD 
i;rAM 10 DUO, LENGTH 10 000, X -0 750, 
Y 0 301, 2 0 230, SWFACT 1 OOO, 
SEN1J 
SWPOD 
DIAM = 10 000, LENGTH 10 000, X -: 300, 
Y = 0 591, Z 0 230, SWFACT = 000, 
SRNIJ 
SFUS 
r.wMAX q 060, 30DL 160 670, FRA& 3 590. 
FflATJQ = '.• FRN = 1 ooc. 
$EKL 
SiNC fNE 
DIAM = 000, N = 4, OUTCOD 3, 
S-KND 
SSSSSS- ,$$$$SS$SS$$S$S$$S$$$SSSS$$$$$$$$$$S$SSS$$$$SSSSJ}SSSSS5J$:3$S$S$$$$$$$$S$ 
STRDATA 
'HKACH 0.990, l.hi
 JP 
- 5000.000, DELMP = 0 200, 
OP-SLF 4,000, IIMAXP - 40OO0.000, I": ':? 0 ODO, 
GMAX = 
••00 .coo, 
SMMAXP 1.100, SMHINP =; 0 200, 
TIMTOl = 5.500, TItlT02 = O.BuU, ULTLF • 9 
• 0 il, WfOKBP 0.010, WPTRAT = 900,000, WFUEL -182720 000, X3E8C - 30.OOO, IBREG o, I PLOT = 2, 
IPSI3E = -3, TPRINT 0, :•
 t--I 
= 
IPST02 = 2, R. •-:}• = 2 TO: :• • = JJCK0SE 
- 2, NLEGCL 0, NLEGLO = 0, 
ACSYNT-IN 
HL£tSCS 0, NMISS = 1, LEMUEL Wf FALSE -
SEND 
S 0 .5QE.+Q5 
MACH WO. ALTITUDE KOH140NTAL NO. V.'.LD 
PHASE START END START RND DIST TT:-' TURN "G"S WKH.'H. M 
IP IX W D 
A p 
CLIMB 0 .50 
p. DO 0 
IDDOO 0. 
0 0 . 0 o.o 250,0 1 oooo 1 2-100 n 0 
1 CLIMB 0 
6U O.OO -1 26000 0. 0 0. 0 0.0 210.0 1 oooo 1 2-100 u 0 
CRUISE 0 .75 0.75 2 3000 -j.
 411 
J . 0 . 0 0.0 
0.0 1 oooo J 4 U 0 0 0 0 CLIMB 50 0.00 0 ioooo ) . <I a. 0 o.o 2=0.0 1 couo 1 2-100 0 0 CLIm 0 • 0 . 00 2800D 0, i
 0 o.o 3J0.O L 2 -1 0 0 0 0 CRUISE 0 0.V5 41000 -1 50D. o o. '•; 0.0 0.0 1 oooo -
4 .J i 0 c 0 ** MCDAC :-i JA TRANSPORT AEHOtlYNAKlCS MODU'F V], * * SACI... 
AB05S 
0,22 0, ALMAX - 20 .ooo. AMC 35.000, BONOSE = 21.060, E-TEF = 1 .ooo. RALOiT = 0.000, RCUAX 1.000, ROC = 0 015, HOCAN 0.020, 
SFVvF = i.ooo. S" IR —, 0 SSO, MACHN 0.750. 
SFANAC 0.090, SWPMAX; = 60 .000. SWPMIN O.OOO, 
xcnc a 0.600, XCDW = 0 6 0, AJCAN • 0, 
ALEU 3, 1 NORM - 1, ISMNDR = 
1SUPCR = 0, ITRAr 0, IXCD - 1, 
I i pc = F ELLIPW CLO o.ooo, 
0.000, 0 000, 0.ODD, 
o.ooo. 0 ooo, 0.000, 
o.ooo, 0 .000, o.ooo
CLOC 
= o.ooo, 0 .ooo, o.ooo, o.ooo. 0 000, o.ooo. 0.ooo 0 .000, o.ooo, 
o.ooo. CLOVT" 0 .000, o.coo, 
o.ooo, 0 ,000, O.0OD, 
0,000, 0 Q00, 0.coy. 
o.' oo, 0 .ooo, CMO 
o.ooo, 
o .ooo. 0 .000, 0-000, o.ooo. 0 .000, )0O, 
o.ooo. 
0 000, o.ooo, 
SMHSWP O.OOl, : .000, o . c •. . , O.-WS, 
.000, o.ooo. 
o.ooo, 0 ooo, 0,000, 
0.000, YSWP 0 . ooo, o.ooo, 
0.000, 0 .000, o.ooo, 
0.ooo. 0 .000, o.ooo, 0.000, 0 , $AN> 
SAMULT 
CSF 1.000, ESSF = 1 .000, FCD = 1.000, 
FCSJF 1,000, FCDL = 1 .000, FCDQ i" 1.000, 
FCDW 
1.00D, 
F'TJWB = 1 .ooo, ?EW3 = 
i,ooo, FTNTF = 1.000, FL&COR 1 .000, FLI 
1,000, 
FLBCOB i.000, Y.R 1 • ill FCCR/'. ]-000, i .0:»o, 1 . Ouu, i.ooo. l.00R., 1 .000, 1.000, 
I. ooo. 1 .ooo, i.ooo. SEND SATRJH 
CANE •J.OcO, CFLAP • 10 .000, CSH _ 0,250, 
IT o.ooo, a.-' = "0 .002, SM - o.ooo. 
SPANF 70.000, z:-G - 0 . 050, IVCAM = 0, 
ITRIM 1, 
1, 1, l. 
1, i. 
1. , i, 
SEND JABOT 
IALF 0, IALF - 2, ICOD - i, 
IPLOT l, HALF 10, NMET1, - •j, 
Al, L" 1.000, 2,000, 
C17-LONG $ DATA BLOCK A 
**** KCDOHWELL OOUULAE C-17 TRANSPORT MISSION -•*'*' 
$ DATA BlVJCK E 
0 0 0 0 0 
S DATA BLOCK V 
15.08:56 
SEND 
SAD RAG 
ICDO 
CDSTR 
SMNCDC 
SMTANK 
SEND 
SATAKE 
CLLANE 
DELFTO 
LDLAND 
SEND 
SAPRINT 
ECHOIN 
C17 
3 000, 4 000, 6 000, 
S 000, 10 000, 12 000, 
14 000, ALTV 0 000, 0 ooo, 
0 000, 0 000, 0 000, 
0 000, c 000, 0 000, 
30000 000, 30000 000, CLINPT 0 000, 
0 000, 0 000, 0 000, 
0 000, 0 ooo, 0 000, 
0 ooo. 0 000, 0 000, 
0 400, 0 500, 0 600, 
0 700, 0 800, 0 900, 
0 700, 0 800, 0 850, 
0 900, ISTRS 0, 0, 
0, 0, 0, 
0, 0, 0, 
0, 0, ITB = 0, 
0, 0, 0, 
0, 0, 0, 
0, 0, 0, 
0, 0, 0, 
0, 0, 0, 
0, 0, 0, 
0, 
0, CDE-MB 0 ooo, 0 000, 
0 ooo, 0 000, 0 000, 
0 000, 0 000, 0 ooo, 
c 000, 0 000, CDONPT 0 000, 
0 000, 0 ooo, 0 000, 
0 000, 0 ooo. 0 ooo, 
0 ooo, 0 000, 0 000, 
0 ooo, 0 000, 0 ooo, 
0 000, 0 000, 0 000, 
0 000, 0 000, 0 000 , 
0 000, CDTNK 0 ooo, 0 ooo. 
0 ooo. 0 ooo, 0 000, 
0 000, 0 000, 0 ooo, 
0 ooo, 0 000, CDEXTR 0 000, 
0 000, 0 000, 0 ooo, 
0 000, 0 ooo, 0 000, 
0 000, 0 000, 0 000, 
0 ooo, 0 000, 0 000, 
0 000, 0 000, 0 000, 
0 000, 0 000, 0 ooo, 
0 000, SMNBMB 0 000, 0 800, 
0 900, 0 930, 0 950, 
0 980, 1 000, 1 100, 
1 400, 1 600, SMSTRE 0 000, 
0 800, 0 900, 0 930, 
0 950, 0 980, 1 000, 
1 100, 1 400, 1 600, 
0 000, 0 000, 0 000, 
0 000, 0 000, 0 000, 
0 000, 0 000, 0 000, 
0 000, SMEXTR 0 000, 0 800, 
0 900, 0 930, 0 950, 
0 980, 1 000, 1 100, 
1 400, 1 600, 
-I 000, CLTO = -1 000, DELFLD 45 000, 
25 000, DELLED 30 000, DELLTO 10 000, 
-1 000, LDTO -1 ooo, 
1, ECHOUT - 0, INTM 0, 
C17-LONG- ACS YNT-IN 
IPBLNT = 0, IPCAN = 0, I PENG 
IPEXT = 0, IPFLAP = 0, IPFRIC 
IPISTF = 0, IPLIFT = 0, IPMIN 
IPWAVE = 0, KERROR = 0, 
SEND 
** C-17 PROPULSION MODULE - USING CF6 ENGINE (CYCLE ANALYSIS) 
SLEWIS 
TWOAB = 
AENDIA 
BA = 5 . 
SCPR 
YREN 
MODPRT 
ALTD 
XMACH 
SEND 
SAFTBD 
SEND 
40700.0, 
•• 6.21, AENLE = 15,5, AENWT = 4200.0, 
I, IPR = 1, SFADP =1.4, SFADSP =1.4 
1.350, 
95.000, 
1, 
0.000, 
30000.000, 
0.200, 
0.650, 
WCWA1 
EN 
HAS 
0.030, 
10000.000, 
40000.000, 
0.400, 
0.750, 
KT5 = 0, 
SFBPP = 
XMDES 
KT7 
NDTAIL 
KODE = 2, 
1.4, ETAF1=0.90. 
1.400, 
= 0, 
6, 
20000.000, 
50000.000, 
0.500, 
0,800, 
C17-LONG- ACS YNT-OUT 
CECCCCC 
C 
C 
C 
: 
C 
CECCCCC 
out) 15 CTO 
0 o 
O Q' 
D 0 
0 D 
QOUDOOO 
PPPRPPP 
p p 
7 P 
PPPPPI>P 
P 
EEi-:i!'ffiE 
E 
EJiEl:. 
SSSi 
S 
L:SSSS 
S 
EEEEEEH SSSSSSi 
SIMttLE ANALYSIS 
OPTIMIZATION 
SENSITIVITY 
TWO-VARIABLE FUNCTION SPACE 
OPTIMUM SENSITI1/ITY 
APPROXIMATE -.-I1MIZATION 
jyTIMATED DATA STORAGE REQUIREMENTS 
INPUT 
9 
REAL 
EXECUTION AVAILABLE 
5000 
INTEKEP. 
EXECUTION 
1 
AVAILABLE 
MOO 
CONTROL PROGRAM 
FOR 
ENGINEERING SYNTHESIS 
TITLE 
' 1 • •'CDOMNHLL if'>ui:,S C-U 'IVRBSPCKT MISSION ***« 
1 CARD IMAGES OF CONTROL DATA 
IMAGE CARD 
1) S DATA BLOCK A 
J) * 1 MCDONNELL DOUGLAS C-17 TRANSPORT MISSION 
3) S DATA BLOCK B 
4) 1 
5) S DATA BLOCK V 
6) END 
TITLE: 
MCDONNELL DOUGLAS C-17 TRANSPORT MISSION ** 
CONTS.QL yAHAMETSR1.-: ; 
CALCULATION CONTROL. 
NUMBER Of GLOBAL DE-SIGN VARIABLES. 
NUMBER OF SEKSITIVITY VARIABLES, 
NUMBER OF PNTFCTIOWS IM W6-SPACE, 
NUKBEh OF APPROXIMATING VAR. 
1HPUT INFORMATION PR3MT COSE, 
DEBUG PRINT CODE, 
CALCULATION COiJTHNCALC 
VALUE MEANING 
NCALC 
NDV 
t*sv 
NZVAK 
•. • APRX 
IPNPUT 
IPDBG 
AAAAAAA CCCCCCC SSSSSSS Y Y N N TTTTTTT 
A A C s r Y NN N T 
A A C S Y y H N N T 
AAAAAAA C SSSSSSS y N N N T 
A A C s Y N N H T 
A A C S Y N N T 
A A CCCCCCC SSSSSSS Y N N T 
NASA-AMES PROGRAM 
FOR 
AIRCRAFT SYNTHESIS 
TITLE 
*«** MCDONNELL DOUGLAS C-17 TRANSPORT MISSION 
AIRCRAFT TYPE - TRANSPORT 
•j LE: 
MCDONNELL DOUGLAS C-17 TRANSPORT MISSION 
AIRCRAFT TYPE - TRANSPORT 
CONTROL PARAMETERS: 
READ CONTROL, 
EXECUTION CONTROL, 
WRITE CONTROL, 
TIMBER j DENTl>'i! INC CONVERGENCE 
VARIABLE FDR CGNVEftOED VEHICLE, 
NUMBER IOBUTIFYING COMPARJKiTJ 
VARIABLE FOR CONVERGED VEHICLE, 
MREAD = 
MEXEc -
MWRITE = 
JOi" = 
= 
3 
5 
57C 
585 
Nov 18 % 
15:0«:5H C17-LONG-ACS YNTOUT 
SUMMARY OUTPUT PRINT CODE, IPSUM - I OIN1TIAL ESTIMATED 
GLOBAL EfiJWft PRINT CODE, KGLOBP = D IF CODE - 1. WEIGHT IS FIXED 
GLOBAL COMMON INITIALIZATION CODE, LNIT = 0 
LitUIJr: PRINT •'.- DE, IPDEG - 2 QUANTITY VALUE CODC QUANTITY VALiJH CODE 
GLOBAL PLOT CONTROL, TGPLT = 0 
DATA TRANSFER INFORMATION FILE, IRDDCR 7 WAF = 174OU0 • WAIRC = I TOO. 0 
DATA TRANSFER INFORMATION PRINT, IFDTR 0 WAPU 222 P WAMMUN = 0. C 
WARM 0 D - - L74C0. 0 
WBB1 0 0 WB0DY - 69600. D 
WCAKD = 0 0 WCAKGO = 50000. 1 
VEHICLE CONVERGENCE INFOKMAT.ON: HCtUflf = 1300 1 WE 34600. 0 
CONVERGENCE TOLEkANCE, TOL = .10000E-O3 ...-.LI 5220 0 W:-;P = 29DO0. 0 
ESTIM FIIIX VS WE*T SLOPE ' .AAOOOH*'JO 7IETANK 0 0 WFEQ 81200. 0 
LuUNDING WEIGHT, WGHAX = .8SDODE'-06 WFS = 4060 0 WCA = 1 740 . 0 
WGrlAR 0 0 WRDP = 4640 . 0 
WHT 4640 0 WINST = 2900 , 0 
WLG = 29000. 0 MISS = 0. 0 
MIA 5S0O 0 WFA = 348D0. 0 
MODULE IDENTIFICATION NUMBERS: WPASS > 87O00 0 '.-.PL 104400. • 
WPS = 46400 0 W3C IL600. 0 
NUMBER MODULE WTSUM 580000. 0 WVT 5800. 0 
1 GEOMETRY W.'ING 46400 0 WL3CMB = 0 , 0 
2 VRA.TEi.'TORY WENVP 0. 0 WPIV O. 0 
3 AERODYNAMICS WLIKTF 0. 0 WHH2 = O. 0 
4 PROPC ISIOK WT'IRV = 0. C 
5 STABILITY ATO CONTROL 
6 WEIGHTS 
S01\:JC BOOM 
9 ECONOMICS 
11 SUMMARY OUTPUT 
|il TAKEOFF AND LANDING 
MODULUS .ARE CALLED FOR INPUT] 
6 12 3 4 
•PHP. FOLLOWING QRDBS: 
MODULES ARE CALL 
1 3 6 
FOR EXECUTION IN THE FOLLOWING ORDER: 
MCOCLFS ARK CAL! ". 70. OUTPUT IN THE FOLLOWING ORDER: 
6 2 3 4 1 
In(j'_L. 1 .: Module # 
1 IKITIM, HEIGHTS INPUT DATA 
ACSYNT MODC'.. K N1 'MBER 6 
AIRCRAFT TYPE: TRANSPORT 
TITLE: •*-' MCDAC C-:7 TRANSPORT *»«*»• 
0CONTROL OPTIONS 
Input tox Models F 1 
Geometry TPPBR Data 
1""" MCD0NNKLL DOUGLAS C-17A TRANSPORT GEOMETRY **** 
2 SWING 
3 AR 
4 LFLAPC 
5 TCROOT 
6 WFFRAC 
7.200, AREA 
0,110, SWEEP 
0.135, TCTIP 
0.800, XWING 
• .OOO, I:; ••• 
25.000, TAPER 
0.107, TFLAPC 
0.290, ZROOT 
IPRINT = 
IDELT = 
KL 
KS 
KB 
FR 
STRESS = 
DPCABIN 
'.HMTEN = 
TECHI 
SLQPEUJ -
StJOPEfSl = 
SLOPE (It) -
1 1GRAPH = 
0 IOBLIQ = 
.00 K2 
. 00 Kb 
,00 KP1 
.00 TKCHG • 
3D0DO. 
5.00 IG3AR 
0 IMTGR 
1.00 1.00 
1.00 1.00 
I.OO T.EO 
I.CO I.OO 
1 ITAIL = 
0 KWING = 
.00 K3 
.00 AFKAC^ • 
.00 KP2 
,00 WGTO 
DENS = 
1 JFLTYP 
1 
i .00 
1 .00 
1.00 
0 KEKi«OR 
0 KHODY 
1.0 K4 
.85 MAXIT 
. 00 
580000. 
.100 F 
1 
1 . 00 
. . 
1 .00 
1 . 0Q 
00 
00 
00 
1, OD 
1 .00 
1,00 
I .OC 
1.00 
I .OO 
O 
I 
1.0 
I 
i. OO 
1.00 
1.00 
.000 
1 .00 
1 .00 
7 KSWEEP 
8 ..,••.•:.) 
9 SHTAIL 
10 AR 
11 SWEEP 
12 TCTIP 
13 KSWEEP 
14 SEND 
15 SVTAIL 
16 AR 
17 SWKKT' 
IB TCROOT 
5.000, AREA 
27,000, TAPER 
0.080, XHTAIL 
1, 
1.000, AREA 
41.000, SWFACT 
0.110, TCTIP 
64i.OOO, CVMT 
0.400, TCROOT 
-0.010, ZROOT 
685.000, CWT 
1.000, TAPER 
-6.000 
0.300 
O. NO 
0.800 
1.000 
0. 090 
1 . 765 
0. 100 
0 .990 
0.110, VTKO 
15:08:58 C17-LONG-ACS YNT-OUT 
19 XVTAIL 
20 KSWEEF 
21 SEND 
22 $WPOD 
23 DIAM 
24 Y 
25 SEND 
2 6 SWPOD 
27 DIAM 
28 Y 
29 SEND 
30 SFUS 
31 BDMAX 
32 FRATIO 
33 SEND 
34 SENGINE 
35 DIAM 
3 6 SEND 
0.871, YROOT 
1, 
10.000, LENGTH 
0.301, Z 
10.000, LENGTH 
0.591, 2. 
21.060, BODL 
0,000, FRN 
B.000, N 
0.000, ZROOT 0. 900, 
10.000, X 
0.230, SWFACT 
10.000, X 
0.23 0, SWFACT 
160.670, FRAB 
1.000, 
4, OOTCOD 
-0.750, 
1 .000, 
-1.000, 
1.000, 
3 . 590, 
33 86 10 53 348 34 
40 26 10 53 348 34 
46 66 10 53 348 34 S3 06 10 53 348 34 59 46 10 53 343 34 65 86 10 53 348 34 
72 26 10 53 348 34 
78 66 10 53 348 34 
85 06 10 S3 348 34 
88 84 10 63 355 01 
92 63 10 69 359 07 
96 41 10 71 360 47 
10C 19 10 69 359 18 
103 97 10 63 355 15 
107 75 10 53 348 40 
111 53 10 39 338 94 
115 31 10 20 326 80 
119 09 9 97 312 05 
122 87 9 69 294 77 
12 6 65 9 36 275 05 
130 43 8 97 253 04 
134 21 3 54 228 89 
137 99 co 03 202 82 
141 77 7 46 175 05 
145 55 6 81 145 86 
149 33 6 07 115 60 
153 11 Ln 19 84 63 
156 89 4 12 53 26 
160 67 2 40 18 10 
END OF GEOMETRY DATA CARDS 
Max. Diameter,. 
Fineness Ratio. 
Surface Area... 
Volume 
Fuselage 
21.060 
7.629 
9511.863 
. 45999.004 
Geometry Initial Output 
Dimensions of Planar Surfaces (each] 
36 LINES READ wing H.Tail V.Tail Canard Units 
Geometry Initial Output 
NUMBER OF SURFACES. 1.0 1.0 1.0 1.0 
Fuselage Definition PLAN AREA 3800.0 845.0 685.0 .0 (SQ.FT. 
SURFACE AREA 6779.8 1696.1 1135.6 .0 (SQ.FT. 
X R Area VOLUME 7 652.7 704 .6 1380.5 ,0 (CU.FT. 
.oo 00 00 SPAN 165 409 65 000 26 173 .000 (FT. ) 
1.05 1 84 10 61 L.E. SWEEP 28 418 30 763 41 082 .000 (DEG.) 
2.11 3 03 28 85 C/4 SWEEP 25 ooo 27 000 41 000 .000 (DEG.) 
3.16 4 03 50 92 T.E. SWEEP 13 601 14 165 40 753 ,000 (DEG.1 
4.21 4 89 75 24 ASPECT RATIO 7 200 5 000 1 000 .000 
5.26 5 66 100 80 ROOT CHORD 35 344 18 571 26 304 . OOC (FT. ) 
6 .32 6 35 126 87 ROOT THICKNESS 57 257 20 057 34 721 .000 (IN. ) 
7.37 6 98 152 87 ROOT T/C 13 5 090 110 .000 
8.42 7 53 178 35 TIP CHORD 10 603 7 429 26 041 .000 (FT. } 
9 .48 8 04 202 92 TIP THICKNESS 13 614 7 131 34 .374 ,000 (IN. ) 
10.53 8 49 226 26 TIP T/C 107 080 110 .000 
11.58 8 89 248 09 TAPER RATIO 300 400 990 .000 
12 . 64 9 24 268 18 MEAN AERO CHORD.... 25 194 13 796 26 . 173 . ooo (PT. ) 
13 .69 9 55 286 34 
14 .74 9 81 302 39 37 758 135 071 113 640 .000 (FT.) 
15 . 80 10 03 316 20 C/4 ROOT AT 46 594 139 .714 120 .216 ,000 (FT. ) 
16.85 10 21 327 65 73 102 153 643 139 .944 .000 (FT.) 
17 .90 10 35 336 65 LE M.A.C. AT 56 118 143 362 125 029 .000 IFT.) 
18.95 10 45 343 13 C/4 M.A.C. AT 62 416 146 .811 131 .572 ,000 (FT. ) 
20 .01 10 51 347 04 TE M.A.C. AT BI 311 157 158 151 .202 .000 (FT. ] 
21.06 10 53 348 34 Y M.A.C. AT 33 93 0 13 929 13 .064 .000 
27 . 46 10 53 348 34 LE TIP AT 82 509 154 416 136 457 .000 [FT. ) 
Nov J 8 5 
15:0$ 5* 
C/4 TIP AT 85.160 156.274 142.967 
TE TIP AT 93.112 161.345 162.498 
ELEVATION 8.424 29.499 9.477 
GEOMETRIC TOTAL VOLUME COEFF .745 .075 
EFFECTIVE TOTAL VOLUME COEFF ,74 5 .075 
C17-LONG-ACS YNT-OUT 
.000 (FT.) 
.000 (FT.) 
.000 (FT.) 
,000 
.000 
EXTENSIONS 
Strake Rear Extension 
Centroid location at .00 .00 
Area .00 ,00 
Sweep Angle .00 
Wetted Area 0 .00 
Volume .00 .00 
Total Wing Area 3800.00 
Total Wetted Area 22219.92 
FUEL TANKS 
Tank Volume Weight Density 
Wing 5292. 264612. 50.00 
Fustl 0. 0. 50.00 
Fus#2 . 0. 50.00 
Total 264612. 
Mission Fuel Required = 182051. 
Available Fuel Volume in Winy - 6615. 
Aircraft Weight = 5BO00O.0OO lbs. 
Aircraft volume = 5573 6.773 cu.ft. 
Aircraft Density = 10.209 lbs./cu.ft. 
ICASE = 4 (Fineness Ratio Method) 
Input for Module # 2 r * * * * * 
***************x** 
TRAJECTORY INPUT 
k ****** * 
TIMTOl = 5.5 MENDUR 0 . NCRUSE 2 IPLOT - 2 
TIMT02 - .5 QMAX = BOO. IPSIZE = -3 HMINP = 0 
FRFURE = .05 XDESC 80.0 IPSTOl = 3 HMAXP = 50000 
DESLF : 6.0C WKFUEL = 1. DOO IPST02 = 2 DELHP = 5000. 
ULTLF = 9.00 CRMACH .990 IBREG = 0 SMMINP = .200 
RANGE = 1000. WKLAND .570 IENDUR = 0 SMMAXP = 1.100 
WFUEL = 182720. FLFAC = .600 IPRINT 0 DELHP = . 200 
WFEXT 0 , DECEL = ,250 KERROR 2 WCOMBP = 
WFTRAP 900. NLEGCL - 0 NLEGCR 0 NLEGLO - 0 
FWGMAX » 1.200 TOL = . 001 MILOOM 0 NMISS = 
NCODE = 
1 0 .01 
HMPROP = 1 
MISSION 1 
MACH NO. HORIZONTAL 
PHASE START END START END DIST TIME 
CLIMB .50 .00 0 10000 .0 .0 
CLIMB .60 .00 -1 28000 .0 , 0 
CRUISE .75 .75 28000 -1 4100.0 .0 
CLIMB .50 . OO 0 10000 .0 . 0 
CLIMB . 60 . 00 -1 28000 .0 .0 
NO. VIND 
TURN -G"S WKFUEL M IP IX W B A P 
.0 250.0 
.0 310.0 
.0 .0 
.0 250.0 
.0 310.0 
1 oooo i 2 -1 0 a 0 0 
1 oooo I 2 -1 0 0 0 0 
1 oooo I 4 0 0 0 0 0 
1 oooo i 2 -1 0 0 c 0 
1 oooo i 2 -1 0 0 c 0 
.75 .75 41000 500.0 .0 .0 . 0 1.0000 1 4 0 0 0 0 0 
Input for Module ft 3 
AERODYNAMIC INPUT DATA 
** MCDAC C-17A TRANSPORT AERODYNAMICS MODULE 
FACTORS INTEGERS AND LOGICALS 
FALEL = 1 .000 ALELJ 3 NALF 10 ABOSB 220 SHK 
= 25 .ooo 
FBLNT = .010 IALF 0 NMDTL = 6 ALMAX = 20 ooo SM 
= 000 
FCD = 1 .ooo IALP 2 ECHOIN = 1 AMC = 35 000 SMNDR 
= .860 
FCDF = 1 .ooo IAXE = 0 ECHOUT = 0 BTEF = 1 000 SWPMA 
X = 60 000 
FCDL = 1 ooo ICDO 0 ELLIPC = F CGM = 250 SWPMI 
N = ooo 
FCDLH = 1 .ooo ICOD 1 ELLIPH = p CLLAND = -1 000 Y0 
= 000 
FCDO = 1 000 I NORM 1 ELLIPW = F CLTO = -1 000 ZCG 
= ooc 
FCDW = 1 000 INTM 0 CSF 1 ooc 
FCDWB = 1 000 IPBLNT = 0 DELFLD 45 ooo 
FCL = 1 ooo I PENG 0 DELFTC 25. 000 
FCLH = 1 ooc IPFRIC 0 DELLED = 30 000 
PDNOSE = 1 000 IPTEXT = 0 DELLTO 10 000 
FENG = 1 ooo IPINTF = 0 ESSF = 1 ooc 
FEXP = 780 IPLIFT 0 EXA = 667 
FINTF 1 000 I PLOT = 1 EXC 2 . ooo 
FLBCOR = 1 000 IPMIN 0 IT = 000 
FLD = 1 000 IPWAVE 0 LDLAND -1 ooo 
FLECOR = 1 ooo ISMNDR = 0 LDTO = -1. 000 
FLNOSE = 1 000 ISUPCR • 0 MACHN 750 
FLSCOR 1 ooc ITRAP = 0 0HOQ1 = ooo 
FMDR 1 010 IVCAM = 0 RCLMAX = 1. ooc 
FSEP = 1 000 IXCD 1 ROC 015 
FTRIM - 1 000 KERROR 0 SFWF = 1. ooo 
ARRAYS 
ALIN ooo 1 . 000 2.000 3.000 4.ooo 6.000 8.000 10 .000 12 .000 
14.000 
ALTV 0. D. 0. 0. 0. 0. 0 . 0 . 30000. 
30000. 
CDBMB = .0000 , oooo .0000 .0000 .oooo .0000 .0000 oooo oooo 
.0000 
CDEXTR = .oooo .0000 .oooo .oooo .oooo .0000 .0000 oooo oooo 
.0000 
CDONPT .oooc . oooo .0000 ,0000 .0000 . oooo ,0000 oooo oooo 
.0000 
CDSTR = .0000 , oooo ,0000 .0000 .0000 .oooo .0000 DOO0 oooo 
. 0000 
CDTNK = .oooo .0000 .0000 .oooo .oooo .0000 .0000 oooo oooo 
.0000 
CLINPT = ooo .000 .000 .000 .000 .ooo .ooo ,000 .000 
C i 7-LONG-ACSYNT-OUT .000 
cuo * 
.ODD 
CLKIN = . ooo 
.ooo FCDRA = 
1.000 
FCLRA = 
1 .000 
FI.DM .; .000 
FVCAM = 
1 .000 
ISTRS = 
0 
I •• 
0 
TTS -0 
l 
SMF.KTR = 
1.600 , 900 SKIMS = 
1.S0O KMJJroo = .OOC 
SMWSI.T" = 
.000 
SUSIES = 
l. eoy 
SMTAMX •¬ 
.COO 
YSHP 
.000 
. 000 
.000 
1.000 l.ooc 
i. ooo 
l .ooo o 
o o 
i .ooo 
.400 
n n ft 
.000 
.000 
.000 . 000 
.000 
.ooo 
,000 i. 00 .J 
i.ooo 
1.000 
1.000 
0 
0 0 
1 
. 800 
.500 . nsc 
.ooc . ooo 
• 80C . ooo 
.ooo 
ooo 
.ooo 
1 .000 
1 . GOu 
1.000 
1 . 000 0 
0 0 
1 
. 900 
.6 
. ooo 
.000 
. 900 
.000 
.000 
.000 
.ooo 
.000 1.000 
1.000 
i. ooo 
1.000 
0 
0 0 
1 
. 930 
.700 
.930 
. 000 .000 
. 930 . 0 00 
. 000 
7? 7 
.000 
.000 i. ooo 
i.ooo 
1 . ooo 
1.000 
0 
0 0 
1 . 950 
. 800 
.950 .ooo 
. ooo .98% 
. 000 
.000 
.ooo 
,000 
.000 
1 . 000 
1.000 
! . :>Oi, 
1 .000 
0 
0 0 
1 
.980 
. 900 
.lie 
.ooo 
.000 
. 980 
, 000 
.ooo Inpj: Cor Module # 4 
+ it***!****.* * -ft t * * > 
.ooo 
,000 
. 000 
1 . COO 
i.ooo 
1.000 l.OO-O 
0 
0 
0 
1 
1 .000 
,700 
1. OOu 
. ooo 
.000 
1 . 000 .000 
.000 
.000 . 7 00 
. 000 
1 0(H) 
1. ooo 
1 . jOO 
1 . 000 
0 
0 
0 
1 
l. loc 
.800 
1. 100 
. ooo 
.000 
1.100 .000 
.ooo 
.000 
,000 
.000 i .ooo 
i. ooo 
1.000 
1.000 
0 
0 
0 
1 
1.400 
1.400 
. 000 
.000 
1 . 400 , 000 
.ooo 
PROPULSION INPUT 
VERSION 04-7 6 
--- • ooo SFSFC2 - 1 .000 SFSfcJ 1 .000 
SMI 500 SODG 1.000 TOSA 518.000 TR « 520 000 THAB 0 . TWOAB = 40700. TWTO = 500 T3 - 2800. TSW 34DD. 
T51 0. T7M 3400. T71 0, VC1 = 980 WCWA1 ^ .03 0 XMDES 1 . 400 WT = 950 YREN 95 FRBT .000 
FRPN - boo RDIAM = 1 . 150 RI -:. ; = 2.000 IPR i rpfciMT = 0 : T, - J _ 0 
K ERROR = 0 KODH • 2 RT5 0 KX7 = 0 HINFR =! 0 NAB = 6 NO/.Z 0 NFROP = 6 NSUKM = 15 
1ENG = 5 ICF6 ) 
THEStl VARIABLES FJjL USED HY TABLE LOOK UP 
ESF = 1.000 HDTAIL = 8 I PFBUG = 
A1TD = 
XMACH = 
XHPBI « KPHJ = 
XHPfcll B .000 
XPRI1 = 
. ooo XM1RT3 = .OUO 
XPRI2 = . 000 
0. 
.200 
.000 
1.000 . ooo 
.000 . ooo 
.000 . 000 .ooo 
. DC"! 
.001 
10000. . 400 
.300 
1 .000 . OOO 
. ooo 
.000 
.000 .ooo .000 
,ooo 
.000 
20000, 
.500 
. 600 
1 .000 
.000 
.000 .000 
.ooo 
30'000 . 
, 550 
,900 
1 . ODD 
.000 . OOC 
.000 
. 000 
400CO. 
. 750 
1.200 
1 .000 .000 
. ooo 
000 
.000 
50000. 
. 800 4
 .0*0 
1.000 
. ooo 
. 000 
oor, 
.000 
. 000 
.000 
.ooc 
.000 
tt** c-17 PROPULSION MO. 
USING CF6 ENGINE (CYCI K ANALYSIS! 
** Bajlft V*tlicl« CGrivercjjriCF. ** 
llHiaated Gross Weight = .5SQOOE + 06 
Col] Ins Moduli: # 1 
Calling Koduls * 2 
IN CRUISE, PHASE 6, LEG 1, THRUST DOES NOT MATCH DRAG WITHIN 3 PERCENT. 
DRAG = .24243E+05 TN = .231IOE+05 
IN CRUISE, PHASE 6, L'iG 2, THRUST DOES MOT MATCH DRAG WITHIN 3 PERCENT , 
DRAG - .2394313*05 TN = .23 ilOF* 05 
Calling N.-.d,il = H 6 
AENUIA = 6 210 aek:.:-: 15 500 AEHWT = 4200 000 Calculated Girr>ss Weight ^ .524iae+06 
ALTI = ooo AM 000 A'lMUfi — 385 Slo] L: Wcalc vs. West 
line = .SOOOOEi-00 MSNTW :G = 
00 0 AWAkSU 157 :-.-. = 5 900 Estimated Gross Weight a .40600E+06 DELPR - ooo DELT57 100 000 LIS PWCC = 2 odd 
ca 1' inc Module 11 1 
DIA1 - 8 200 EAB1 - 750 • u = 940 Calling Module fl 2 
EDI 75f'. ETftCl = B20 E7AF1 = 900 
Cal 1 Inn noil-, .e # 6 
ETAT1 = S 2 0 HI.. = 3( HVT' 86U0 Calculated Gross Vfeiyht = . 43924E-I-06 
MACHJ 1 0 00 MACH2 - 1 ice ?C FAC = 1 coo 
Slope o£ Wcalr VF . We:it 
line F .48816E+00 
POSA 29 
9.20 
PRFD = 1 560 PWCC 100 00D 
P11P1 1 72 0 P2P1 - 30 000 R.10A = 1 000 Estimated Groes W&i^ht 
= ,47094E*0S R32 §40 R54 = 940 H54N = 920 Calll.na
 MLidula k 1 R7I1 9ao 
R711N = 9EO SCPR 1 350 Calling Module » 2 
SFADP = 1 1 SFADSP - 1 400 SFAUXP = 1 )00 
Calling Module 4 6 
5K8F.P 1 ODD SFBPP - 1 400 EFBTP = 1 000 Ciluulatud Ore SB W«iyl:*: = .4G9'74E*0S 
SFDltfp - 1 
01 1 1 000 IL' = 1 000 Slope ol Hcalc vs. Wsist line = .479fi7F*00 
"smJ C17 -LONG-ACS YNT- OUT 
Passenger Service 0. 0. 00 No 
Estimated Gross Weight = . 46863E+06 Cargo Containers 8000 , 3629 . 1 71 No 
Calling Module # 1 
Calling Module # 2 Operating Weight Empty 236079. 107085. 50 38 
Calling Module # 6 
Calculated Gross Weight = .46861E+06 Fuel 182533, B2797. 3B 95 
** End Vehicle Convergence Payload 50000. 22680, 10 67 No 
Passengers ( 0) 0 . 0. 00 No 
3 Convergence Iterations Required Baggage 0 , 0. 00 No 
***************************** ************************************************* Cargo 50000. 22680. 10 67 Yes 
Calling Module # 1 
Calling Module ft 2 Calculated weight 468611. 212562 . 100 00 NO 
Calling Module # 6 
Estimated Weight 468628. 212570. 
Percent Error ,0C 
Output for Module # 6 
*********************** ******** 
weight Statement - Transport 
**** MCTJAC C-17 TRANSPORT ****** 
Qmax: 
Design Load Factor: 
Ultimate Load Factor: 
Structure and Material: 
Wing Equation: 
Body Equation: 
800. 
6 . 00 
9 . 00 
Aluminum Skin, Stringer 
Sanders Equation 
Sanders Equation 
Component Pounds Kilograms Percent Slope Tech Fixed 
Airframe Structure 180447. 818S1. 38 51 No 
wing 78036. 35397. 16 65 1 00 1 00 No 
Fuselage 56583. 25666. 12 07 1 00 1 00 No 
Horizontal Tail ( Low) 11508. 5220. 2 46 1 oc 1 00 No 
Vertical Tail 7027 . 3188. 1 50 1 00 1 00 No 
Nacelles 6024 . 2732 . 1 29 1 00 1 00 No 
Landing Gear 21269, 9648. 4 54 1 00 1 00 NO 
Propulsion 21672. 9830. 4 62 No 
Engines ( 4) 19992. 9068. 4 27 1 00 1 oc NO 
Fuel System 1680. 762 . 36 1 oc 1 00 NO 
Fixed Equipment 23459. 10641. 5 01 1 00 No 
Hyd & Pneumatic 2812 . 1275, 60 1 00 No 
Electrical 3707 . 1681. 79 1 oo NO 
Avionics 1807 . 820 . 39 1 oo No 
Instrumentation 1025. 465. 22 1 00 No 
De-ice & Air Cond 0. 0. 00 1 oo No 
Aux Power System 668. 303. 14 1 00 No 
Furnish k Eqpt 9420 . 4273 , 2 01 1 00 NO 
Seats and Lavatories 0. 0. 00 1 00 No 
Galley 0. 0. 00 1 oo NO 
Misc Cockpit 0 . 0 , oc 1 00 No 
Cabin Finishing 6620. 3003 . 1 41 1 00 NO 
Cabin Emergency Equip 0. 0. 00 1 00 No 
Cargo Handling 2801. 1270. 60 1 00 No 
Flight Controls 4021 . 1824. 86 1 00 NO 
Empty Weight 225579. 102322. 48 .14 
Operating Items 0. 0. .00 No 
Flight Crew ( 0} 
1500. 680. .32 Yes 
Crew Baggage and Provisions 100. 45 . .02 No 
Flight Attendents ( 0) 0. 0. .00 No 
Unusable Fuel and Oil 900, 408 . . 19 NO 
No* 18 96 
15:08:58 C17-LONG-ACSYNT-OUT 
Output for Module # 2 
**********************! ****************** 
TRAJECTORY OUTPUT 
MISSION 
PHASE 
(PAYLOAD 50000. LB) 
M 
SFC(I) 
SFC(U) 
THRUST(I) 
THRUST(U) 
CL 
CD 
CDINST 
ALPHA 
GAMMA 
L/D 
WFUEL 
W 
THR/THA 
TIME 
WA 
PR 
VEL 
Q 
x 
WARM-UP 0. 4902.8 5 50 
.33 162800. 
TAKEOFF . 24 0, 2 0236 12 00 450.1 50 270 
.41 134541. 4551 1 91 463274.9 1408 90 87 
.41 134541. 0031 4 45 1.00 1 00 4781 
2ND SEG .24 400 . 2 0236 12 00 270 
.41 100905. 4551 6 09 463274.9 1406 90 87 
.41 134541. 0031 4 45 1. 00 1 00 
Landing Field Length (ground run) = 2562. ft 
Weight for Landing calculation = 364584. lbs 
Landing Thrust to Weight ratio = .3 81 
Takeoff Weight = 468628. lbs 
Landing Weight  294787. lbs 
CLIMB .46 10000. .5712 5 01 1890.5 to 34 491. 
,50 89427. .0352 7 60 461384.4 1096 13 212. 
Cycle .49 90853. . 0018 16 22 1 .00 1 00 11. 
CLIMB .82 28000. .3778 7 64 4395.0 7 45 825. 
.65 48237. .0322 1 05 456989.5 721 40 326 . 
Cycle , 63 49995. .0014 11 73 1.0C 1 00 55. 
CRUISE .75 28000. .3225 2 38 147237.0 542 83 753 . 
.68 21971. ,0213 00 309752.5 576 46 271, 
Cycle .64 23362. .0013 15 12 .45 1 00 4034 . 
CLIMB .46 10000. .3765 3 24 1122.6 1 39 491. 
.50 89427. .0243 13 08 308629.9 1096 13 212 . 
Cycle .49 90853. .0018 15 52 1.00 1 00 6 , 
CLIMB . 82 28000. .2473 1 71 2301.3 3 85 B25. 
.65 48237. .0277 2 61 306328.6 721 40 326 , 
Cycle .63 49995. . 0014 B 93 1.00 1 00 28 . 
CRUISE .75 41000, ,5308 4 00 11541.3 64 94 726 . 
.60 17606. .0314 OC 294787,3 340 44 148 . 
Cycle ,57 18380. .0014 16 92 . 61 1 00 466. 
LANDING .21 0 . 2.5886 12 00 230 . 
.39 138858. , 9702 14 63 364584.2 1395 37 63 . 
.39 139686. .0035 2 67 1.00 1 OC 5283 . 
Fuel Summary 
Total Fuel 
Mission Fuel 
Reserve Fuel 
Trapped Fuel 
183433. 
173841. 
8692 . 
900. 
Takeoff Fuel: 
Warmup -
Takeoff = 
Fuel Load: 
4903. External = 0. 
450. Internal = 183433. 
Block Time = 10.480 hrs 
Block Range  4600.0 n.m. 
Block Fuel  173840.5 lb. 
4781. ft 
5283. ft Decel @ .250 Gs 
C17-LGNG-ACS YNT-OUT 
Detailed Aerodynamics Output 
Output for Module # 3 
ft**************************************************** 
Mach = .85 
ftltitude = 30000. 
Parasite Drag 
Takeoff Configuration; Flaps and Slats 
Induced Drag 
Friction .0111 Alpha Cl Cd L/D Cm e Cdtrim Deltrim 
Zone 
Body 
2 
.0050 0 784 ,2249 3 5 .000 , 15 .0050 -4.2 
Wing 2 .0038 1 0 934 .2418 3 S .000 .19 .0067 -5.1 
Strakes 
2 
.0000 2 0 1 078 .2595 4 2 .000 ,23 .0087 -6.0 
H. Tail 
2 
,0014 3 0 1 220 .2792 4 4 ,00C .28 . 0109 -6.9 
V. Tail .0008 4 0 1 357 .3004 4 5 .000 .31 .0132 -7.7 
Canard .0000 6 0 1 621 .3470 4 7 .ooo .38 . 0181 -9.4 
Interference 
2 
.0031 8 0 1 614 .3777 4 3 . 000 ,34 .0137 -9.6 
Wave . 0266 10 0 1 772 .4558 3 9 .ooo .33 . 0189 -11.1 
3 
External .0000 12 0 1 705 .4814 3 5 .000 .29 ,0262 -13.0 
Tanks .0000 14 c 1 792 .5702 3 1 .ooo . 27 . 0366 -15.0 
4 
Bombs 
Stores 
Extra 
Camber 
.0000 
. 0000 
.OOOC 
. 0000 
Cdmin 
ft 
Mach 
Altitude 
Slope Factors 
Cl/Alpha (per radian) 
Cdl/C1A2 
Alpha Transition Zone 2-
Flap Setting 
Slat Setting 
Flap Type Single 
4.1226 
.1649 
7 .065 
25. 
10. 
519. sq. 
,9C 
30000. 
Parasite Drag 
Landing Configuration: Flaps and Slats 
Induced Drag 
Friction 
Zone 
Body 2 
.0110 
.0050 
Alpha 
.0 1 
Cl 
293 
Cd 
, 6474 
L/D 
2.0 
Cm 
.000 
e 
.13 
Cdtrim 
.0130 
Deltrim 
-6.8 
Wing 
n 
.0038 1 0 1 456 .6788 2 1 .000 .16 .0155 -7.6 
c 
Strakes .0000 2 0 1 613 .7093 2 3 .ooc .18 .0183 -8.4 
A 
H. Tail 
2 
.0013 3 0 1 767 .7411 2 4 . 000 .21 .0211 -9.2 
V. Tail ,0008 4 0 1 917 .7740 2 5 ,ooc .24 . 0241 -10.0 
i. 
Canard 
2 
.0000 6 0 2 206 .8428 2 6 . 000 .28 ,0302 -11.6 
Interference .0023 3 0 1 721 ,5598 3 1 .000 ,28 . 0154 -10.0 
Wave ,0719 10_ 0 1 853 . 6396 2 9 .000 .27 .0214 -11.6 
4 
External .0000 12 0 1 972 .7289 2 7 .ooc .27 .0293 -13 .4 
4 
Tanks .0000 14 0 2 082 .8289 2 5 .ooo .26 .0400 -15. 4 
4 
Bombs 
Stores 
Extra 
,0000 
.0000 
. 0000 
Slope Factors 
Cl/Alpha (per radian) 
Cdl/Cl"2 
Alpha Transition Zone 2-
3.2262 
.1716 
3 6.514 
.0852 
Flat Setting 
Slat SettitlQ 
Flap Typo 
C17-LONG-ACS YNT-OUT 
Single 
'5. 
30. 
519 . 
Detailed Aerodynamics: 
Altitude = 0. 
Output 
Parasif.^ Dia.j 
Friction 
tane 
B iv 
2 wing 
2 
Strikes 
H. Tail 
2 
V. Tail 
2 
Canard 
2 
Intarfcrence 
2 
Wave 
External 2 
Tanks 
2 
•ibs 
Eh ores 
Extra 
Cairier 
.0118 
, 0053 
, 0041 
,0000 
. 0014 
,0009 
. oooo 
. 0042 
.0000 
. oooo 
.0000 . oooo 
. oooo 
. oooo 
.oooo 
cdmin 
Mr'ich = 
Altitude = 
Parasite Drag 
Frier i nn 
Zone 
tody 
2 
Wi ng 
Strakes 
;i. Tail 
2 
V. Tail 2 
Canaid 
2 
Ijit«rf erance 2 
Wave 
2 
External 
2 : 
3 
Storea 
Extra 
. 50 
0 . 
. one 
.0053 
. 0040 
. oooo 
.0014 
.0009 
.oooo 
.•042 
.0000 
.0000 
.oooo 
.oooo 
.0000 
. oooo 
Induced Drag 
Alplia '-. 
. 0 
1.0 
2.0 
3 .C 
4 . 0 
6.0 
8 .0 
.000 
.118 
. 233 
.3 45 
.454 
.665 
.867 
10.0 1.060 
12.0 1.246 
14.0 1.424 
Induced Drag 
Alpha Cl 
.0 
1. 0 
2.0 
3.0 
4.0 
6.0 
8.0 
10 . 0 
12 .0 
.000 
. 121 
.240 
.355 
.468 
. 685 
.892 
1 . 090 
1 .280 
14.0 1.433 
Cd L/D 
.OlfG 
.0168 
.0 
7 . C 
0192 12.1 
.0230 15.0 
.0282 16.1 
.0424 15.7 
.0611 14.2 
.0840 12.6 
.1107 11.2 
.1410 10.1 
Cm 
.ooo 
. ooo 
.ooo 
. ooo 
.ooc 
.000 
. ooo 
.ooc 
. ooo 
e cdtrim Deltrim 
.00 
.76 
.75 
.75 
.75 
,74 
.74 
.73 
.72 
. 72 
. coon 
.0001 .0004 
. 0008 
. 0014 
.0030 
.0052 
.0077 
.0107 
. 0140 
-1 . 6 
-2 . 4 
-3.1 
-4 . 6 
-6.2 
-7 . 7 
-9.3 
-11. . 1 
Slope factors 
Cl/Alpha (per radian) 5.82J3 
Cdl/cl"2 .0616 
Alpha Tranaition Sone 2-3 16.894 
Programmed Flap SuLting 0. 
Flap Type 
Cd L/D 
.0159 .0 
.0167 7.3 
12.5 
.0232 15.3 
,0M? 16.3 
.0436 15.7 
.0632 14.1 
.0872 12.5 
.1150 11.1 
.325 7 4.4 
Single 
Cm 
. 000 
.000 
.000 
.000 
.000 
.000 
.000 .ooo 
.01:0 
.000 
.00 
.76 
. 76 
.76 
.76 
.75 
,74 
.7-5 
.73 
.29 
Cdtrim Delt 
0000 
.0001 
.0004 
. 0009 
.0015 
.0033 .005b 
. 003 j 
.0116 
. D161 Slopa
 Factors 
Cl .'Alpha (pur radian i 5.86H 
Cdl/Cl"2 .1509 AIJJDJI
 Transition Zone 2-3 13,323 
15:08:58 
C J 7 - LONG - ACS YNT- O U T 
Camber .00DD 
ft 
.015S 
eraordrntjied vlap set tins 0. 
Flap !'YPA Single 519. sq. 
Detailoa Aerodynamics Ou'j:-jt 
Mach = 
Altitude = 
Parasite Drag 
Frit'- i on 
Bftdy 
2 
King 
?. 
Strikes 
2 
H. Tail 
2 
V. Tail 
2 
Ci.- 2 
2 
Irktcr.f r.rence 2 
Wave 
2 
External 
Tar.ks 
BE: bs 
States 
fcXtra 
Camber 
Cdnin 
0. 
. 0115 
.0052 
.0040 
.oooo 
.0014 
. QD03 
.0000 
. 0042 
. oooo 
.oooo 
.0000 
.0000 
. oooo 
. oooo 
.iii 
Induced Drag 
Alpha 
. 0 
1.0 
2.0 
3.0 
4 .0 
6.0 
B.O 
Cl 
.ooo 
.126 
.250 
.370 
.487 
. 712 
.927 
10.0 1.132 
12.0 1.277 
14.0 1.407 
Cd 
.015! 
. 0167 
L/D 
.0 
7 . 6 
.0193 12.9 
.0236 15.6 
.0295 16.5 
.0453 15.7 
.0662 14.0 
.0916 12.4 
.2501 5.1 
.3249 4.3 
Cm 
.000 
. 000 
. OOC 
. ooo 
.ooo 
. ooo 
.ooo 
. ooo 
.000 
. ooo 
e Cdtrim Deltrim 
.00 
.77 .11 
.77 
.76 
.76 
. 75 
.75 
.31 
,28 
.0000 
. 0001 
.0004 
. 0010 
.0017 
. 0036 
.0062 
.0092 
.0125 
. 0 
- .9 
-1 . 7 
-2 . 6 
-3.4 
-5 . 1 
-6.8 
-8.5 
-10. 4 
-H7 
M-I^ Factors 
Cl/Alpha (por radian) 
Cdl/Cl"2 
Alpha Transition Zone 2-3 
Piogran^.ied Flap Ssttiny 
.0153 fjap Type Sim; j e 
5,7573 
.1562 
10.880 
0. 
519. 3q. 
Mach = 
Al tit-vide = 
Parasi v Dra^f 
Friction 
Zone-
Body 
2 
Wing 
2 
Strakes 
2 
H. Tail 
2 
V. Tail 
2 
Canaid 
2 
\. • ••[,-r-i.ce 
2 
Wave 
3 
Exteri:a 1 
3 
Tanks 
3 
>.oiobs 
STORES 
Extra 
.70 
0. 
.01 13 
. 0052 
.0039 
.0000 
.0014 
. 0009 
.oooo 
, .••" I. 
.0000 
.0000 
. •:: OT 
.0000 
.ooi • 
.O^'O 
Induced 
Alpha 
. 0 
1.0 
2 . C 
3 .0 
4 . 0 
6.0 
8.C 
10.0 
12.0 
14 . 0 
Drag 
Cl 
.000 
. 133 
.263 
.390 
.513 
.750 
.975 
1 .Mi 
1.298 
1.435 
Cd 
. 0156 
.0166 
.0195 
. 1903 
. 3U2 
. 3412 
L/D 
. 0 
8.0 
13.5 
.0242 16.1 
.0306 16.8 
0478 15.7 
.0705 13.B 
6.0 
5.0 
4.2 
Cm 
.000 
. OOC 
. OOC 
. OOO 
,000 
.00,; 
. OOC 
000 
. OOD 
.000 
.oc 
. 79 
.78 
.78 
.78 
. 77 
.77 
. 33 
. 30 
.28 
Cdtrim Dsltiiis 
. 0000 
. 0001 
. 0005 
.0011 
. '.y. '•. 9 
.0041 
.0069 
.0/857 
. 9134 
.0197 
.0 
- .9 
-1. 8 
-2 .7 
-3,6 
-5.4 
-7 . 1 
-S . 7 
-IO. 4 
-12.2 Slope Factors 
Cl/Alpha Lper radian! 5.6T43 
CDI/CI*A .1580 
Alpha Transit lull Zone 2-3 9.077 
Nov 18 96 
15,08:58 
Camber 
Cdmin 
ft 
.0000 
. 0156 
Programmed Flap Setting 
Flap Type Single 
C17-LONG- ACS YNT-OUT 
Detailed Aerodynamics Output 0 . 
519 . Mach 
Altitude = 
Parasite Drag 
Friction 
Zone 
Body 
2 
Wing 
2 
Strakes 
2 
H. Tail 
2 
V. Tail 
2 
Canard 
2 
Interference 
3 
Wave 
3 
External 
3 
Tanks 
3 
Bombs 
Stores 
Extra 
Camber 
.80 
0. 
.0112 
.0051 
. 0039 
.0000 
. 0014 
,0008 
.0000 
. 0041 
.0016 
.oooc 
. 0000 
.oooo 
.0000 
. oooo 
,0000 
Induced Drag 
Alpha Cl Cd L/D Cm a Cdtrim Deltrim 
.0 000 .0168 ,0 . 000 .00 . oooo .0 
1.0 143 .0179 8.0 .000 .80 .0002 -1.0 
2.0 283 .0212 13 .3 .000 . 80 .0006 -2.0 
3.0 419 .0265 15.8 .000 ,80 .0013 -2.9 
4 . 0 551 .0337 16.4 .000 .79 .0022 -3.9 
6.0 804 .0530 15.2 . ooo ,79 .0048 -5 .7 
8.0 1 042 .1337 7.8 .000 .41 .0077 -7.9 
10.0 1 189 .2052 5.8 .000 .33 .0108 -9.2 
12 .0 1 342 .2793 4.8 .000 .30 .0163 -11 .0 
14 . C 1 482 .3649 4.1 . ooo .28 . 023 5 -12 . 8 
Slope Factors 
Cl/Alpha (per radian) 
Cdl/Cl"2 
Alpha Transition Zone 2-3 
Programmed Flap Setting 
Cdmin 
ft 
Mach 
Altitude = 
Parasite Drag 
, 0168 
.90 
0. 
Flap Type Single 
6.0661 
. 1585 
7 . 667 
0. 
519. sq, 
Induced Drag 
Friction 
Zone 
Body 
2 
.0110 
.0050 
Mpha 
.0 
Cl 
ooo 
Cd 
.0852 
L/D 
. 0 
CM 
.000 
e 
.oo 
Cdtrim 
.0000 
Del trim 
.0 
Wing .0038 1 0 159 .0866 1 8 ,000 . 83 .0002 -1 .1 
2 
Strakes 
2 
.0000 2 0 315 .0905 3 5 .000 .82 .0007 -2.1 
H. Tail .0013 3 0 465 .0969 4 8 .000 .82 .0016 -3 .1 
£ 
V. Tail . oooa 4 0 612 . 1054 5. B ,ooc . B2 .0027 -4.2 
Canard .oooo 6 0 893 . 1285 6 9 .000 .81 .0058 -6.2 
2 
Interference .0023 8 0 1 082 .2440 4 . 4 .000 .33 .0131 -9.5 
Wave 
* 
.0719 10 0 1 189 .3036 3 . 9 .000 .29 .0195 -11 .3 
External ,0000 12 0 1 285 . 3720 3. 5 .000 .25 .0280 -13 .3 
Tanks .0000 14 0 1 371 .4496 3 . 1 .000 .23 .0396 -15.5 
Bombs 
Stores 
Extra 
.0000 
.0000 
,0000 
Slope Factors 
Cl/Alpha (per radian) 
Cdl/Cl~2 
5.6120 
, 1938 
Alpha Transition Zone 2-3 6.514 
Nov 1S<* ; 15M.SS 
C17-L0NG-ACS YNT-OUT 
Camber . oooo Programmed Flap Setting 0. 84. 2645. 2837 .848 ,791 .0012 
82. 1947. 2142 . 932 .847 .0012 
Cdmin .0852 Flap Type Single 519. sq. 80. 1200, 1393 1 . 191 1 .025 .0012 
* ft 78 , 330. 507 3 .284 2 .141 , 0011 
.650 30000. 100. 9500, 9738 .562 .548 .0013 
Output Eor Module * 4 98 . 8387 , 8624 .561 ,546 . 0013 
******* ************** * ******** ******* * * * ********** ****** ********************** 96, 7289 . 7523 ,566 .549 .0013 
1 ENGINE SUMMARY 94 . 6196. S426 .580 .560 ,0013 
92 . 5091. 5317 .610 .584 .0013 
90. 3947 . 4166 , 674 .639 , 0012 
ENGINE DIAMETER 6 .21 FEET 88. 2716. 2919 .830 .773 .0011 
ENGINE LENGTH 15 . 50 FEET 86 . 2160, 2379 .874 ,793 .0012 
ENGINE WEIGHT = 4200 ,00 POUNDS 84. 1689. 1910 . 920 .814 .0012 
BYPASS RATIO 5 .90 82 . 1210 . 1432 1 .037 .877 .0013 
NO OF ENGINES - 4 . 80. 710 . 928 1 .393 1 .064 . 0012 
DRAG REF AREA = 3800 ,00 SQ FEET 78 . 158. 359 4 .723 2 .080 .0011 
PWCC PERCENT OF ENGINE CORRECTED AIRFLOW 
THRUST ENGINE THRUST { POUNDS PER ENGINE) 
SFC ENGINE SPECIFIC FUEL CONSUMPTION .750 4O000, 100, 6061 . 6257 .537 .569 . 0013 
THRUSTU - THRUST PER ENGINE IN LBS, W/O INSTAL DRAG CORR 98 . 5330. 553C .589 .568 ,0014 
SFCU = SFC.l/HR, W/O INSTALLATION DRAG CORR 96 . 4613 . 4816 .597 .572 ,0014 
CDINS -TOT INSTALLATION DRAG COEF PER A/C (SWING REF) 94. 3906 , 4110 , 614 .583 .0014 
1 92 . 3201. 3402 .647 .609 .0014 
90 . 2483 . 2679 .714 ,662 .0013 
88 . 1727 . 1915 .870 .785 .0013 
86 . 1358 . 1563 . 926 ,804 .0014 
MACH ALT PWCC THRUST THRUSTU SFC SFCU CDINS 84. 1042 , 1252 ,993 .827 ,0014 
82 . 730. 937 1 . 145 .891 , 0014 
80 . 408 . 609 1 .608 1 .077 .0014 
.200 0. 100 33535. 33712 .404 .402 .0031 78. 66 . 250 7 . 569 1 .987 .0013 
98 32172. 32320 ,420 .418 .0026 
96 29097. 29232 .421 .419 .0024 
94 25361. 25484 .422 .420 .0022 .800 50000, 100. 3823 . 
3356 
3973 
3 510 
.612 
, 615 
.589 
. 589 
.0014 
. 0015 9 2 
90 
213.3 7 . 
16654. 
2144 6 
16747 
.434 
.477 
.431 
.474 
. G &19 
.0017 96. 2899 . 3055 . 625 .593 .0015 88 9877, 9948 .682 ,677 .0013 94. 2449 , 2607 . 644 .605 .0015 
86 7781. 7852 .726 .720 .0013 92. 2002 , 2160 ,681 .631 .0015 
84 6421 . 6494 .727 .719 .0013 90 . 1550. 1706 .753 .6B4 ,0015 
32 5000 . 5073 .757 .746 .0013 88. 1079. 1231 .916 .803 ,0015 
80 3417. 3488 .876 ,858 .0013 86 . B42. 1006 .983 ,822 .0016 
78 1362. 1418 1.679 1 . 613 .0010 84, 636. 807 1 .072 .344 .0017 
82 . 437 . 606 1 .259 .908 ,0016 
80. 234, 398 1 .845 1 , 086 .0016 
.400 10000. 100 21985. 22251 .494 .488 .0017 78. 23 . 173 14 .339 1 .887 .0015 
98 20100. 2O350 . 498 . 492 .0016 
96 17660. 17900 .498 . 491 .0015 
94 15177. 15404 .505 .497 .0015 SEA-LEVEL STATIC THRUST = 40700. (MAX! 
92 12582. 12793 ,527 ,518 .0014 SEA-LEVEL SFC = .328 
90 9735. 9928 . 584 .572 .0012 
B8 6298 , 6470 .766 .745 .0011 
86 5072 . 5246 .797 .770 .0011 
84 4094 . 4273 .815 .781 .0012 Output for Module # 1 
82 3077 , 3258 . 878 . 829 ,0012 ************************* ******* * n * * n * * * * * **** * * * * ***** 
30 1983. 2163 1.075 .985 .0012 
78 665 . 825 2.440 1 .969 . OOIO Fuselage Definition (Type 2) 
21. 060 
1 . 000 
,500 20000. 100 14674. 14920 .523 .515 .0015 Constant Section Length 64 . 005 
98 13028 , 13268 ,520 ,511 .0015 Afterbody Length. 75. 605 
96 11388. 11622 . 522 . 511 ,0014 Afterbody Fineness Ratio 3. 590 
94 9737 , 9960 .532 .520 .0014 Overall Length... 160. 670 
92 8036 . B248 . 557 .543 . 0013 Maximum Diameter. 21, 060 
90 6218. 6417 . 617 . 597 ,0012 2956. 015 
88 4140. 4324 .785 .752 .0011 
B6 3324. 3511 .819 .775 .0012 FUSELAGE CROSS SECTION SIZING TO ACCOMODATE PAYLOAD 
Nov IS 96 
15:08:58 C17 -LONG-ACS YNT- OUT 
PAYLOAD WIDTH OOOOE + 00 
PAYLOAD HEIGHT OOOOE+OO 
THICKNESS OF WING ROOT 4.771 
MAX THICKNESS OF WING FOR FREE FIT OOOOE+OO 
DIAMETER REQUIRED FOR WIDTH OF EMBEDDED ENGINES.. .OOOOE+OO 
DIAMETER REQUIRED FOR HEIGHT OF EMBEDDED ENGINES. -OOOOE+OO 
DIAMETER REQUIRED TO ENCLOSE BOX 4.771 
REQUIRED DIAMETER. . (MAX OF 3 ABOVE) 4.77
RADIUS OF ENGINE POD 3.975 
ANGLE OF ENGINE PLACEMENT (ABOVE HORIZONTAL) 2300 
STAND-OFF DISTANCE (NON-DIMENSIONAL) 301
STAND-OFF DISTANCE (FT.) 1.196 
LOC. OF CENTER OF ENGINE 7.557 
AIRCRAFT INTERNAL ARRANGEMENT 
ITEM LENGTH INITIAL FINAL ACTUAL 
STATION STATION DIAM 
RADAR .000 .000 .OOO .000 
ENGINE . 15.500 .000 15.500 .000 
NOSE LENGTH 21.06 
AFTERBODY BEGINS AT 85.0
OVERALL LENGTH 160.7 
MAX. AFT FUEL LOCATION 122.9 
DELTAX DOE TO PAYLOAD AFTERBODY MISMATCH .... 1000. 
DELTAX DUE TO PAYLOAD-F'OVERLAP 1000
DELTAX DUE TO FINENESS RATIO RHQ 64. 0C 
ACTUAL-REQUIRED CREW DIAMETER 21.06 
ACTUAL-REQUIRED PAYLOAD DIAMETER 16.29 
ACTUAL-REQUIRED POWER PLANT DIAMETER -10.94 
WING ROOT THICKNESS IN BODY 4.771 
FUSELAGE WALL THICKNESS OO0OE+00 
VOLUME OF FORWARD FUEL OOOOE+0
VOLUME OF REAR FUEL OOOOE+0
ACTUAL-REQUIRED FUEL VOLUME 1624. 
REQD 
DIAM 
. 000 
-138.246 
Fuselage Definition 
X R Area 
00 00 00 
1 05 1 84 10 61 
2 11 3 03 28 85 
3 16 4 03 50 92 
4 21 4 89 75 24 
5 26 5 66 100 80 
6 32 6 35 126 87 
7 37 6 98 152 87 
3 42 1 53 178 35 
9 48 6 04 202 92 
10 53 8 49 226 26 
11 58 8 89 248 09 
12 64 9 24 268 18 
13 69 9 55 286 34 
14 74 9 81 302 39 
15 80 10 03 316 20 
16 85 10 21 327 65 
17 90 10 35 336 65 
18 95 10 45 343 13 
20 01 10 51 347 04 
21 06 10 53 348 34 
27 46 10 53 348 34 
33 86 10 53 348 34 
40 26 10 53 348 34 
46 66 10 53 348 34 
53 06 10 53 348 34 
39 46 10 53 348 34 
65 86 10 53 348 34 
72 26 10 53 348 34 
78 66 10 53 348 34 
85 06 10 53 348 34 
88 
92 
84 
63 
10 
10 
61 
66 
3 53 
356 
92 
88 
96 41 10 66 357 19 
100 19 10 63 354 81 
103 97 10 55 349 72 
107 75 10 43 341 96 
111 53 10 27 331 53 
115 31 10 07 318 49 
119 09 9 82 302 92 
122 87 9 52 284 92 
126 65 9 18 264 60 
130 43 8 78 242 12 
134 21 8 32 217 66 
137 99 7 81 191 45 
141 77 7 22 163 76 
145 55 6 55 134 90 
149 33 5 79 105 27 
153 11 4 90 75 33 
156 89 3 81 45 54 
160 67 2 07 13 51 
Nacelle Definition Nacelle Location 
x-Xnose R Area X Y 
.00 3 97 49 .63 30 30 24 89 
7 .75 3 97 49 . 63 30 30 -24 39 
23.25 3 97 49.63 43 48 48 88 
31.00 3 97 49 . 63 43 48 -48 B8 
Fuselage 
Max. Diameter 21.060 
Fineness Ratio 7.629 
Surface Area 9434.115 
Volume 45419.180 
Nacelles -
7 . 949 
774.161 (each) 
C17-L0NG-ACSYNT-0UT 
Dimensions of planar Surfaces (each Output for Module § 11 
************ ft*********************** ************** ******* *************** 
Wing H. Tail v.Tail Canard Units 1 SUMMARY ACSYNT OUTPUT -- - NASA, AMES RESEARCH CENTER 
NUMBER OF SURFACES. 1 .0 1.0 1.0 1.0 4 ENGLISH UNITS -
PLAN AREA 3800.0 3 45.0 685 .0 .0 (SQ.FT.) .... MCDONNELL DOUGLAS C-17 TRANSPORT MISSION ***** « 
SURFACE AREA 6779.8 1696.1 1135.6 .0 ISQ.FT. ) 4 DISTANCES IN FEET 
VOLUME 7652 .7 704.6 1380,5 .0 (CU.FT.) 
SPAN 165 409 65 .000 26.173 .000 (FT. ) 4 WEIGHTS IN LBS. 
L.E. SWEEP 28 418 30 .763 41.082 ,000 (DEG.) GENERAL FUSELAGE WING HTAIL VTAIL 
C/4 SWEEP 25 DOO 27 . 000 41.000 .000 (DEG.) + FORCES IN LBS. 
T,E. SWEEP 13 601 14 ,165 40.753 . 000 1DEG.) 
ftSPECT RATIO 7 200 5 .000 1. 000 .000 4 PRESSURES IN LBS/FT**2 
ROOT CHORD 35. 344 IS .571 26.304 .000 (FT. ) WG 468611. LENGTH 160.7 fcREA 3800.0 845 . 0 685.0 
ROOT THICKNESS 57 . 2 57 20 .057 34,721 .000 (IN. I W/S 123.3 DIAMETER 21.1 WETTED AREA 6779.8 1696.1 1135.6 
ROOT T/C 135 .090 .110 .000 T/W .35 VOLUME 45419.2 SPAN 165.4 65 .0 26.2 
TIP CHORD 10. 603 7 .429 26.041 .000 (ET. ) N(Z} ULT 9,0 WETTED AREA 9434.1 L.E. SWEEP 28.4 30.8 41.1 
TIP THICKNESS 13. 614 7 . 131 34.374 .000 (IN. ) CREW 0. FINENESS RATIO 7.6 C/4 SWEEP 25.0 27.C 41.0 
TIP T/C 107 ,080 . 110 .000 PASENGERS 0. ASPECT RATIO 7 .20 5.00 1.00 
TAPER RATIO 300 .400 .990 .ooo TAPER RATIO . 30 .40 .99 
MEAN AERO CHORD .... 25. 194 13 .796 26.173 000 (FT. ) ENGINE WEIGHTS T/C ROOT .14 .09 .11 
T/C TIP . 11 .08 .11 
LE ROOT AT 37. 758 135 .071 113.640 .ooo (FT. > NUMBER 4 , W WG ROOT CHORD 35.3 18. 6 26.3 
C/4 ROOT AT 46. 594 139 , 714 120.216 .000 (FT. ) LENGTH 15.5 STRUCT. 180447. 38.5 TIP CHORD 10,6 7.4 26.0 
TE ROOT AT 73. 102 153 ,643 139.944 .000 (FT. ) DIAM. 6.9 PROPUL. 21672. 4.6 M.A. CHORD 25.2 13 .8 26.2 
LE M.A.C. AT 56 . 118 143 .3 62 125.029 .000 (FT. ) WEIGHT 4200.0 FIX. EQ. 23459. 5.0 LOC. OP L.E. 37.8 13 5.1 113 .6 
C/4 M.A.C. AT 62 . 416 146 , 811 131.572 000 (FT. ) TSLS 40700. FUEL 183433. 39.1 
TE M.A.C. AT 81 , 311 157 . 158 151.202 ooo (FT. ) SFCSLS .33 PAYLOAD 50000. 10,7 
V M.A.C. AT 33. 930 13 .929 13.064 000 
LE TIP AT 82 . 509 154 .416 136.457 000 (FT. ) 
C/4 TIP AT 85. 160 156 274 142.967 000 (FT. ) MISSION SUMMARY 
TE TIP AT 93 . 112 161 845 162.498 000 (FT. ) 
ELEVATION 8 , 424 29 499 9.477 000 (FT. ) 
PHASE MACH ALT FUEL TIME DIST L/D THRUST SFC Q 
GEOMETRIC TOTAL VOLUME LUTL'T 
EFFECTIVE TOTAL VOLUME COEFF 
. 745 
745 
. 075 
.075 
000 
000 TAKEOFF .00 0. 5353. 6.0 4781.3 
CLIMB .46 10000. 1891. 2.3 10.7 16.22 89426 6 .502 212 
CLIMB .82 28000. 4395. 7.4 55.4 11.73 48236 8 .648 325 
E X T E N S I O N S CRUISE .75 28000. 147237. 542.8 4033.9 15.12 21971 1 .685 271 
Strake Rear Extension CLIMB .46 10000. 1123. 1.4 6.2 15.52 89426 6 .502 212 
Centroid location at. .00 .00 CLIMB ,82 28000. 2301. 3.8 28.2 8.93 48236 8 .648 325 
.00 .00 CRUISE .75 41000. 11541. 64.9 465.6 16.92 17605 9 .597 147 
Sweep Angle .00 LANDING 5283.3 
.00 .00 
.00 .00 Block Time = 10.480 hr (without air and ground manuever allowances) 
Block Range - 4600.0 ran 
Total Wing Area 3 iOO.00 
Total Wetted Area.... 22142.1 8 
FUEL T A N K S 
Tank Volume Weight Density 
Wing 5292. 264612 50 . 00 
Fusil 0 0 50 ,00 
Fus#2 . 0 SO .00 
Total 264612 
Mission Fuel Required 183433, 
Available Fuel Volume : • Wing - 6615. 
Aircraft Weight = 468627.812 lbs. 
Aircraft Volume = 55156.949 cu.ft. 
aircraft Density = 8 . 49 6 lbs./cu.ft, 
ICASE = 4 (Fineness Ratio Method) 
Appendix E Page 58 
Appendix E. C17 FLOPS Input & Output File 
15:09:03 C17-SHORT-FLOPS-IN 
C17 Short Mission 
SOPTIOM 
MPRINT=1, 
IOPT=l, 
IANAL=3, 
NOPRO=0, 
NOISE=0, 
ICOST-0, 
IFITE= 0, 
INENG-1, 
ITAKOF=0, 
ILAND=0, 
$END 
SWTIN 
MYWTS=0, 
LTLF=2 .25, 
SPAN=167.4, 
FCOMP=0.15, 
NETAW=2 , 
ETAW=0.0, 1.0, 
CHD=32.82, 13.13, 
TOC=0.135, 0.107, 
ETAE=0.301, 0.591, 
SHT'845.0, 
SWPHT=27 .0, 
ARHT-5,0, 
TCHT=0.085, 
HHT=1., 
SVT-685.0, 
SWPVT=41.0, 
ARVT=1.0, 
TCVT=0.11, 
NFIN=2, 
SFIN=72.55, 
ARFIN-1.09, 
TRFIN=0.325, 
SWPFIN=50.0, 
TCF1N=0.10, 
XL=159.1, 
WF=21,06, 
DF=23 .00, 
NEW>4, 
NEF=0, 
WENG=7100., 
XNAC=12.23, 
DNAC=6.23, 
FULWMX-182720.0, 
FULFMX=0.0. 
NFLCR=3, 
CARGF=1,, 
CARGOF=124000.0, 
SEND 
SCONFIN 
DESRNG=2500., 
KTVC=1.0, 
VTVO0 , 10, 
GW-=650000 . , 
THRUST=40700., 
AR=7.2, 
SW=3800.0, 
SWEEP=25.0, 
TCA=.121, 
VCKN=0.75, 
CH-45000.0, 
SEND 
SAERIN 
MYAERO=0, 
AITEK=1.2 
VAPPR=115 
FLTO=4400., 
FLLDG=3200. 
CLTOM=3.585 
SEND 
SENGDIN 
IGENBN=1, 
IDLE=1, 
NONEG=l, 
IXTRAP=0, 
DFFAO0 . , 
EMACH=0.80, 
SEND 
o, 
0.7S, 0.70, 0.60, 0.50, 0.40, 0.30, 0.20, 0.10, 0.0 
SENGINE 
I£NG=2, 
IFILE-'TFNSEP' 
TFILE='ENGTAB' 
OFILE- ' ENGOUT 1 
OPRDES=30.8, 
BPRDES=5.9, 
TETDES = 2 8O0. , 
YEAR=1995 . , 
IGVW=-1, 
SEND 
SMISSIN 
FACT=1.0, 
1SKAL=1, 
MSUMPT=1, 
IATA=0, 
IFLAG-2, 
IRW=1, 
ITTFF-1, 
TAXOTM=15.0 
TAK0TM=2.0, 
TAXITM=2.0, 
NCLIMB=1, 
CLMMIN=0.3, 
FWF»-1., 
IFAACL=0, 
IFAADE=0, 
NCRUSE=1, 
IOC=2, 
CRMMIN=0.3 , 
CRMACH=0.75 
CRALT=28000 
IVS=1, 
IRS=1, 
TIMMAP=2.0, 
ALTRAN=500. 
SEND 
START 
CLIMB 1 
CRUISE 1 
RELEASE 
REFUEL 
CRUISE 
DESCENT 
END 
2000. 
124000. 
-2000, 
500. 
105 . 
Nov 18 96 
i 
e NAMELIST SOPTION 
PROGRAM CONTROL, EXECUTION, ANALYSIS AND PLOT OPTION DATA 
DESCRIPTION NAME VALUE DIMENSIONS 
TYPE OF PROBLEM IOPT 1 
ANALYSIS OPTION IANAL 3 
MAIN ENGINE DECK SWITCH INENG 1 
DETAILED TAKEOFF SWITCH ITAXOF 0 
DETAILED LANDING SWITCH ILAND
COST CALCULATION SWITCH ICOST 0 
TRANSPORT/FIGHTER SWITCH IFITE
TAKEOFF PROFILE FOR NOISE NOPRO 0 
PROFILE OUTPUT FILE SWITCH NPFILE
NOISE CALCULATIONS SWITCH NOISE 0 
MASTER PRINT CONTROL MPRINT 1 
XFLOPS DATA PLOT SWITCH IXFL 0 
AERO POLAR PLOT SWITCH IPOLP
THRUST DATA PLOT SWITCH IPLTTH 0 
HISTORY DATA PLOT SWITCH IPLTHS
EXCESS POWER PLOT SWITCH IPLTPS 0 
» NAMELIST SWTIN 
GEOMETRIC, WEIGHT, BALANCE AND INERTIA DATA 
DESCRIPTION NAME VALUE DIMENSIONS 
MAX OPER MACH NUMBER VMMO .0000 
ULTIMATE LOAD FACTOR ULF 2,2500 
REF WEIGHT NUMBER NWREF 39 
CG REFERENCE LENGTH CGREFL 1909.2 
X FOR START OF CGREFL CGREFX .C 
SWITCH TO COMPUTE WEIGHTS MYWTS C 
DESIGN GROSS WT. (RATIO) DGW 1.OOC 
HYDRAULIC SYSTEM PRESSURE HYDPR 3000. 
IN 
IN 
WING DATA 
DIHEDRAL(POSITIVE) 
GLOVE AND BAT AREA 
SPAN 
DIH 
GLOV 
SPAN 
CONTROL SURFACE AREA RATIO FLAPR 
FRACTION OF COMPOSITES FCOMP 
AEROELASTIC TAILORING FACT FAERT 
STRUT BRACING FACTOR 
VARIABLE SWEEP FACTOR 
FSTRT 
VARSWP 
.000 
-92.05 
167.40 
.3330 
.1500 
.0000 
.0000 
. 0000 
DEG 
SQ FT 
FT 
DETAILED WING DEFINITION DATA FOR 2 STATIONS 
STATION DATA 1 to 
0 Y/SEMISPAN ETAW 0000 1.0000 
0 CHORD/SEMISPAN CHD 32 8200 13.1300 
0 THICKNESS/CHORD TOC 1350 .1070 
0 LOAD PATH SWEEP SWL .00 .oo 
0 REFERENCE ASPECT RATIO ARREF 7.20 
REFERENCE THICKNESS/CHORD TCREF . 12100 
FRACTION OF LOAD ON DEFINED 
WING (OR REF WING AREA] PCTL 1.0000 
NO. OF INTEGRATION STEPS NSTD 50 
FLOPS-OUT 
ENGINE LOCATIONS 
LOAD DISTRIBUTION CONTROL 
HORIZONTAL TAIL DATA 
AREA 
1/4 CHORD SWEEP ANGLE 
ASPECT RATIO 
TAPER RATIO 
T/C 
LOCATION ON VERTICAL TAIL 
VERTICAL TAIL DATA 
NUMBER OF VERTICAL TAILS 
AREA 
1/4 CHORD SWEEP ANGLE 
ASPECT RATIO 
TAPER RATIO 
T/C 
WING FIN DATA 
AREA 
ASPECT RATIO 
TAPER RATIO 
T/C 
1/4 CHORD SWEEP ANGLE 
NUMBER OF FINS 
FUSELAGE DATA 
NUMBER OF FUSELAGES 
TOTAL LENGTH 
MAXIMUM WIDTH 
MAXIMUM DEPTH 
CARGO AIRCRAFT FACTOR 
PASSENGER COMPART LENGTH 
LANDING GEAR DATA 
LENGTH OF MAIN GEAR 
LENGTH OF NOSE GEAR 
DESIGN LANDING WEIGHT 
SET WLDG TO END OF DESCENT 
CARRIER BASED AIRCRAFT 
PROPULSION SYSTEM DATA 
NUMBER OF ENGINES ON WING 
NUMBER OF ENGINES ON FUSE 
BASELINE ENGINE THRUST 
BASELINE ENGINE WEIGHT 
WEIGHT SCALING PARAMETER 
BASELINE INLET WEIGHT 
INLET WT SCALING EXPONENT 
BASELINE NOZZLE WEIGHT 
NOZZLE WT SCALING EXPONENT 
BASELINE NACELLE LENGTH 
BASELINE NACELLE DIAMETER 
FUEL CAPACITY OF WING 
(FUEL CAPACITY FACTOR 
FUEL CAPACITY OF FUSELAGE 
ADJUST FUSE FUEL CAPACITY 
AUXIL TANK FUEL CAPACITY 
NUMBER OF FUEL TANKS 
ADDED MISC PROP SYSTEM WT 
CREW AND PAYLOAD DATA 
FIRST CLASS PASSENGERS 
TOURIST PASSENGERS 
STEWARDESSES 
GALLEY CREW 
ETAE . 3010 
PDIST 2 .00 
SHT 845,0C SQ 
SWPHT 27.00 DEG 
ARHT 5.00 
TRHT .0000 
TCHT .0850 
HHT 1 .0000 
NVERT 1 
SVT 685.00 SQ 
SWPVT 41 .00 DEG 
ARVT 1.0000 
TRVT .0000 
TCVT .1100 
SFIN 72 .55 SQ 
ARFIN 1.090C 
TRFIN .3250 
TCFTN .1000 
SWPFIN 50.00 DEG 
NFIN 2 
NFUSE 1 
XL 159.10 FT 
WF 21 .06 FT 
DF 23 .00 FT 
CARGF 1.0000 
XLP 120.01 FT 
XMLG .00 IN 
XNLG .00 IN 
WLDG 528125.0 LBF 
MLDWT 0 
CARBAS .00 
NEW 4 
NEF c 
THRSO . 0 LBF 
WENG 7100.0 LBF 
EEXP 1.15000 
WINL .0 LBF 
EINL i.ooooo 
WNOZ .C LBF 
EMOZ 1.00000 
XNAC 12 .23 FT 
DNAC 6 .23 FT 
FULWMX 182720.0 LBM 
FWMAX 17.506) 
FULFMX .0 LBM 
IFUFU 0 
FULAUX .0 LBM 
NTANK 7 
WPMISC ooo LBF 
NPF 0 
NPT 0 
NSTU -1 
NGALC -1 
(CALC) 
STITLE, BEGIN INPUT DATA ECHO 
C17 Short Mission 
Nov 18 96 
15:09:06 C17-SHORT-FLOPS-OUT 
PLIGHT CREW NF1.CR 
WIGHT PER PASSENGER MP PASS 
A»i •• ? !• AVENGER SPP 
CAyuo IN WING CARGOW 
CARGO IN FUSELAGE CARGO P" 
ITVUSr-i IDE PARAMETERS FOR WEIGHTS 
WING - TOTAL FKWl 
WING WEIGHT FIRST TERM S-'RWIl 
WING WEIGHT SECKID TERM FRWI2 
WING WEIGHT THIRD TERM 
HORIZONTAL TAIL FKH'F 
VERTICAL TAIL FRVT 
WU. ) W:-.. • FIN FRF IN 
CANARD ••• RCAN 
F0SELAG3 FRFU 
NOSE LANDING GEAR FRLGN 
HI IK LANDING GEAR FPLUM 
NACELLES - TOTAL OR FRNA 
Alt. ;NlJU(.-RTON SYSTEM 
T]]R"JST REVERTERS - TDTAL W'J'HR 
M.-5C PROPULSION SYSTEMS WPMSC 
FUEL SYSTEM WFSYS 
SURFACE CONTROLS FRSC 
AUXILIARY POUHft [/H]T WAPU 
INSTRUMENT GROUP WIN 
HTfiUWUiJCS GROUP W1IYD 
ELECTRICAL CROLJt1 WE 11 EC 
AVIONICS GROUP IvAVON
AP.MAHr-JJT GSOUP WAR* 
FURNISHINGS GBOU?P WPURN 
AIR C0MDITIQM1W3 GROUP MAC 
ANTI-L:"[NG GROUP OR WAI 
AUXILIARY OEM 
UNUSABLE FUEL 
ENGINE OIL 
PASSENGER SERVICE QH AMNO 
AND NONFIXED WEAPONS 
CAittJO AND LAGGAuE CONTAIN. 
OR HISCELL. USEFUL LOAD 
AUXILIARY FUEL TANKS 
FLIGHT L'kSW AND BAQTSAI.E 
CABIN CREW AND BAGGAGE 
HORIZONTAL CENTER OF GRAVITY 
WING 
HORIZONTAL TAIL 
V • CAL TAIL 
WINE VERTICAL FINS 
CANARD 
NCSE LAi.DINC GEAR 
HAIN LAUDING GEAR 
TWO FORWARD ENGINES 
CHE OR TWO AFT ENCflNKS 
AUXILIARY POWER UNIT 
AVIONTQS OFTOUP 
ARMAMENT GROUP 
FUOKT CREW 
PASSENGERS 
CARGO/EXT STORES 
:-AF :, EX s\: 
FUSELAGE FUEL 
WING FUEL 
AIR JHOUCTIOtt S*tt 
AIR CONDITIONING 
IN KING 
IN FUSS 
WUF 
WOIL 
WSP.V 
WCON 
KAUXT 
WEI • ••• • 
LATA 
CGW 
CGE'l 
CGVT 
CUFIN 
CGCAN 
CGF 
L'ULGN 
C'GLGM 
CGEF 
r-CEA 
CGA? 
TGAV 
IA—: 
CGSCR 
C! ' 
CGCW 
r.'CCF 
CfiSWP 
CG.FWF 
CON 
CGAC 
J 
165.0 
10.0 
.0 
OOOO 
oooo 
0D00 
JOOO 
oooo 
ODOO 
oooo 
oooo 
oooo 
oooo 
oooo 
oooo 
.0000 
l.oono 
1.0000 
1 .0000 
i .oooo 
1 .0000 
I . ODDD 
loooo 
1.000 ;l 
. 00OD 
1.0000 
1 . 0DO0 
i .oooo 
1 .0000 
1.0000 
i. oooo 
l.Oi. ID 
i. oooo 
1 . oooo 
1 . oooo 
. 0 
. 0 
. 0 
.0 
. 0 
.0 
.0 
.0 
.0 
. 0 
. 0 
.0 
. 0 
. 0 
. 0 
. 0 
.0 
. 0 
. 0 
. o 
. 0 
LEF 
L6F 
IN 
FN 
IN 
IN 
IA 
IN 
IN 
IN 
IN 
IN 
IN 
IN 
: i 
:-! 
IN 
:N 
IN 
IN 
ADXEUAitY GEAR CGAI 
AUXILIARY TANKS CUAUT 
ANMO AND NONFIXED GUNS CGAMMO 
KlRCKI.LANFOi'S USEFUL LOAD COKIS 
0 IN 
o 
. o IN 
, 0 IN 
IT MANELIST SCONFM 
GSCMETHli; RATI US. OBJECTIVE FUNCTION FACTORS, AND DESIGN VARIABLES 
DESCRIPTION NAME 
DESIGN RANGE OfLSRNG 
WING LOADING REQUIRED V1SR 
THRUST/WEIGHT REQUIRED TKR 
GLOVE/WING AREA BjtfpJJiREQ PGLOV 
MORI2 TAIL VOLUME CQEP HTVG 
VERT TAIL VOLUME COEF VTVC 
COST CALCULATION SWITCH ICOST 
FtlrJr.'T]ON TO BE OPTIMIZED - OBJ 
ACHML/T1 + 
8 LONS) 
DESIGN VARIABLE DATA 
VARIABLE 
SCALE FACTOR 
NAME 
RAMP WEIGHT, LBF GW 
.00000 
WTNG ASPECT RATIO AR 
.00000 
THRUST PER ENGINE, LBF THRUST 
.00000 
REF WING AREA, SQ FT SW 
,00000 
WING TAPER RATIO TR 
.00000 
WTMS 1/4 CHORD SWEEP, DEG SWEEP 
,00000 
WTHU T/C TCA 
.ooooo 
CRUISE MACH NUMBER VCMN 
.00000 
MAX CRUISE ALTITUDE, FT CH 
.00000 
TURBINE INLET TEMP (R) 
.00000 
OVERALL f RE.SSI.'HF. RAT I !j EOPR 
. OOOOO 
FAN PRESSURE RATIO EFPR 
.00000 
•YPASS RATIO EBPR 
.00000 
THROi'TLE RATIO KTi'K 
.U0ODO 
VALUE J-HENSIONS 
25Q0.0 N MI 
.00 
.00000 
19 •> 
. 1OO0O0 
0 
.0000*(RAMP WEIGHT) 
. 0000'RANGE + .001 
1 . 0000 -FUEL + . 000O* 
TfiST H .0000*(NOX EH1 
VALUE ACTIVITY LOWER BOUND UPPER BOUND 
650000.0 
7.2000 
40700.0 
S i u u, o 
.ooooo 
25 . 00 
. 12100 
.75000 
45000.0 
,0C 
. ooc 
.0000 
, of.NO 
noooo 
.0 
.0000 
.ooo 
. 0 
. ooooc 
. 00 
.ooooo 
.ooooc 
c 
.00 
.000 
.0DOO 
.0000 
.00000 
.0 
. D000 
. on 
.ooooc 
.oo 
. 00000 
. ooooo 
, 0 
. 00 
. 0o.j 
. oooo 
.0000 
. 0<OO/1 
# NAnftLI.RT 3 A£p t N 
ARR.ODYNAMIC OPTIONS AND APPROXIMATE TAKEOFF AND LANDING DATA 
DESCRIITION VALUE DIMENSIONS 
Nov 18 
15:09:06 
AERODYNAMIC INPUT METHOD 
WAVE ORAO IMWTT SWITCH 
WAVE DRAG FACTOR 
LINEAR/PARACOLIC INTERP 
AERO MATRIX FORMAT SWITCH 
MAX CAMPER AT 70 ?ERCEMT 
SEMISHAN 
AIRCRAFT BASE AREA 
WIN" ' JO'.OCV 
MODIFY EDET DATA 
FIXED DESIGN CL 
TIJHILLLFLJLWNVLAHLTLFTR FLOW 
AERO EFFICIENCY FACTOR 
MY AERO 
1WAVE 
... ,.t 
. >AER 
IBO 
CAM 
SDA5E 
AITE* 
MODARO 
FCLDES 
XI.t.AM 
LL 
OVERRIDE PJLKAKST kk.S FOR WETl'ky AjiKAS 
WING WETTED AREA SWETW 
B0«. TAIL WETTED AREA SWETH 
VKKT. TnlL WETTED AREA 5HETV 
FUSELAGE WETTED AREA SWETP 
NACELLE WETTED AREA SWETH 
TAKEOFF AND LANDING DATA 
RATIO OF MAX. LANDING WT. 
TO MAX 
LANDING 
TAKEOFF 
MAX 
MAX 
MAX 
MAX 
MAX 
TAJCSOFF WT. WRATIO 
VELOCITY VAPPR 
FIELD LENGTH l"LTO 
[ " . LJING FIELD LENGTH i-i.LLG 
CL TAKEOFF CONFIG. CLTOM 
CL 1-AN IN CONFIG. CLL' M 
APPRCACJI CL ClA^P 
A Iii DENSITY RATIO DFATIO 
L/D RATIO 2ND SEE. CLIMB ELODSS 
L/O RATIO MISSED AEPPOACH ELODMA 
THRUST PER ENGINE TAKEOFF THROFF 
THRUST PER ENGINE 2ND 
YS\. <-| !•• • THRSS 
THRUST PEH T.NGINE MISSED 
APPROACH THRMA 
t NAMELIST SENGDlJJ 
ENGINE DECK CONTROL, SCALING AND USA 
DESCRIPTION 
EhX~.:NL JECK PRINT COKTHOL NGPkT 
ENGINE DECK SOURCE SVJITCH ICFNEW 
SLOPE FACTOR EOS 
EXTRAPOLATING FrJEL FLOWS EXTPftC 
SUBSONIC FUEL FLOW FACTOR FFF5UB 
SUPERSONIC FUEL FLOW FACT FPFEUP 
FLIGHT IDLE SWITCH IDLE 
IGNORE NEGATIVE THRUSTS NONEG 
MIN i:>L>: FUEI FLOW r RACV Y I HMTN 
MAX IDLE FUEL FLOW FRACT FIDMAX 
SFC EXTRAPOLATION SWITCH IXTRAP 
PART PDWrK IV,TA SWITCH IF ILL 
MAX. CRLilSE POWER SETTING MAXCR 
BOOST ENGINE SWITCH DOOST 
FJFL FLOW SCALING 
CONSTANT TERM 1 • • : 
FUEL FLOW SCALING 
LINEAR TtFM AC 
NITROGEN OXIDES SWITCH MOX 
INSTALLATION DRAI3 SWITCH INSCFG 
-SHORT-FLOPS-OUT 
KALTH N'.Jnii:Hk ,,N:I \:.WW~\YY. FOX ENGINE DECS GENERATION 
MACH ALTITUDES 
.80 
.75 
.30 
. 20 
. 10 
.oo 
-1. 
-1. 
1. 
-1. 
# NAMELIST SENGINE 
KN;:I^K •:YI-:.E-: ANALYSIS RU™IT7 DATA 
DESCRIPTION 
2-COMP SEP FLOW TURBOFAN 
ENGINE CYCLE DEF. FILE 
IENG 
IFILE 
VALUE DIMEN: 
COMPONENT MAP TABLES FILE TFILS 
PRINT LEVEL INDICATOR 
PRINT VIB/ANOPP DATA NPRINT 0 
• PRINT LET/EL FOR WEIGH IHTPI r 1 
PLOT ENGINE SCHEMATIC IWTFLT 0 
CYCLE ANALYSIS OUTPUT FILE Ol ... E ENGOUT 
! : ,\G 'I") CENE. VTW. A Dl IK GkKDEK F 
SWITCH FOR WEIGHT CALCS NGINWT 0 
l*,&*y?tNlS, S^l+INT.^1 Vt2+Tjarwi,l.lr. d_ 
PART POWER DATA CONTROL 1THROT 1 
NUMBER OF A/B POINTS NPAD 0 
NUMKXR ;;>- DRY POINTS :. DRY 15 
PART POWER THRUST CUTOFF XTDLE .05000 
MAX ALLOWABLE ITETtATlONS KITMAX 50 
DESIGN POINT DATA 
L^SIOU POINT NET THRUST DFISPW 40700.0 LBF 
OVERALL PRESSURE RATIO =RDFS 30.8000 
FAN PRESSURE RATIO FPRDE3 1.5000 
BYPASS RATIO K.-3 5,9000 
DESIGN TURBINE INLET TEMP 1 ETDJBS 2800.0 DEG R 
DESIGN THBOTTLE RATIO TTRBES 1.0000 
OTHER ENGINE CONFIGURATION DEFINITION DATA 
FLAG FOR At-l-ESIitJkNKk ;,i- i:-N F 
FLAG FOR DUCT BUHNER lliURN F 
AFTERBUSNER EFFICIENCY EFFAB .aiooo 
MAX AFTSR&ypNKR TEMP TAEMAX 3500.0 DIE[j K 
FLAG FOR VARIABLE NOZZLE VEN F 
CUSTOMER COMPRESSOR BLEED C03TBL 1.0000 i.B'SEC 
TURBINE COOLlNU (IRON UK] WC00L -.0001 FKA '" 
CUSTOMER POWER F.XTRACTICW HPEXT 2oa.oo HP 
FUEL HEATING VALUE FHV 13500.0 BTU/LD 
TECHNOLOGY AVAILABILITY YEAR 199$. YEAH 
FLAG TO DO BOAT.*.:!, DRAG : >AT J. 
DELTA TEMPERATURE DTCE . 00 DEG C 
BVZ-Y- VARIES TO ZERO AT ATC J00OO. PT 
FLAG TO DO fPJLLAGE DRAG SPILL p 
FLAG TO DO LIP DRAG LIP 
(OR I 
Nov 18 
15:09: C17-SHORT-FLOPS-OUT 
USED TO DEFINE HACH-ALTITUPE ARHAY PPINT5 
MAXIMUM MACH NUMBER XXKAX .7500 
MAXIMUM ALTITUDE JUQtX 45000. 0 
INCREMENT IN MACH NUMBER XMINC .2000 INCrRUFNT
 1H ALTITUDE AIKC 5000.0 
MINIMUM DYNAMIC PRESSURE OMIN 1 ' i . J 
MAXIMUM DYNAMIC PRESSURE QMAX 1200.00 
ENGTNR CYCLE OPT IMTV.rti'. IN CF.1ITSE CONDITION 
MACH NUMBER 
AT g T TUDE XM3ES 
XADES ENGINE CYCLE BEHAVIORAL CONSTRAINTS MAX COHFRESH DISCHARGE TMP CDTHAX 
MAX CCHPKESR DISCHARGE PRS COPMAX 
MAXIMUM JET VELOCITY VJMAX 
y. IN I MUM SPECIFIC THRUST STMI.N 
MAXIMUM BYPASS/CORE AREA ARMAX 
S£A LEVEL STATIC MAXIMUM THRUST 
GENERATED PROPULSION SYSTEM WT. 
.7500 
41500.0 
99939.0000 
99999.0000 
93939.0000 
1.0000 
99999,0000 
40700.0 
7500.0 
FT 
FT PSF 
psf 
R p;;j 
FT/SEC L3/LB/SEC 
La ) 1 
(NEW BASELINE ENGINE THRUST - GVERRTDEB THRSO) 
ft /.r.I. PO^H'l ENGINE DECK SUMMARY 
MACH = . BOO, ALTSTUiJfc = 40000. . TKH"STS' tr'UEL FLOWS/SPCS/NOX RATIOS FOLLOW 5064.8
 4405.2 3779.3 3469.7 3169.2 2851.9 2535.6 2244.9 1977.3 1730.0 
:502.4 1393.9 1103.1 917.8 741.8 .0 
3142.1 2B21.3 24B.9.9 J331-6 21*0.8 2025.4 1872.7 1731.9 1601.6 1430.9 
136U.9 1165.0 1161.4 1077.2 991.6 629.3 
.628 .640 .E59 .672 .-.38 .710 .739 .771 .810 .856 
.ill .975 1.059 1.174 1.335 .000 
MACH = .800, ALTITUDE = 35000., THRUSTS/FUEL FLOWS.'.SFCS/NOX KATIOS FOLLOW 
6*1"'.9 S60B.1 41-11.J 4417.2 4034. 6 3 630.6 3224.0 2B57.9 L7.2 2202.4 
IS 12.7 1147,2 14(14,4 1168.5 94S.5 .0 
i'-iA.l j: -.'I 31/. -i ;--'"0.8 .-'7:.7 2580.6 2386.0 2206.7 2040.7 1HR6.8 
1744.; mi, a ijse.7 1S372.5 1263.7 sex. a 
.629 .641 .659 .673 .689 .711 .739 .772 .81/ . bi.7 
.912 .978 1.060 1.175 1.336 .000 MP.ch
 = .800, ALT 1 WE = 30000., THRUSTS/FUEL FL0WS/3FCS/MOX RATIOS FOLLOW HIc.:.4
 7100,2 6091.4 5592.5 5108.1 4596.6 4046.B 3616.3 31H7.0 2784.3 
242 .•' 2085.'. 1778.1 1479.4 1.197.2 .0 
£25! .2 4655.4 4 LOR.7 3347.4 3598.6 3)42.J 3090.1 2857.8 2642.9 2443.6 
2258.8 2087.4 192-1.1 ".777.5 1S36.6 1C34.4 
.643 .656 .675 .666 .704 .727 .756 ,790 .829 .876 
353 1.001 1.084 1.201 1.367 .000 
NAGH = .800, ALTITUDE = 21.000.. THRUSTS/FUEL FL0WS/SFCS/NOX RATIOS FOLLOW 
10227.4 SS9S.4 7613 . 6 70!;6.0 6-°°.6 5758. R 5120.1 4533.2 3995.8 J493.3 3(133.J
 2611!.7 2227,6 1P33.4 1499.9 .0 
6/30.3 5966.7 5240.9 4931. J. 4612.2 4-:»J.S 3!J60.b 3662.8 jiJ,.3 3131.9 
2895.0 2675.3 2471.1 227H.2 209 ;.=, 1330.9 
.668 .671 .690 .704 .721 .744 ,774 .80" .848 .897 
.954 1.024 I 107 :,:'.:9 i.^*8 .000 
i/AC'I = . BOO, AMTTJrsS » 30000., 1HH UST?/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
12701.3 11047,1 9477.6 8701,3 7547.6 7151,8 6358.6 5629.7 4958.6 4338.3 
3767.7 3244 '; i7C5.5 2301 .7 1862.7 .0 
8550.0 75/9.9 6689.7 t>264 .4 b8a9.3 5441.7 5031-3 4653.1 4303,1 3978.6 
3677.3 1398.7 >339.2 2894.3 2664.i I690.B 
.673 .646 .706 .720 .737 .761 .791 .827 .868 .917 
.976 1.047 1.13$ 1.257 1.431 .000 
»A/::i - .1(00, ALTITUDE = 15000. . THRUSTS/FUEL FLOWS/SFCS/NOX P.ATJOE FOLLOW 
1065J.7 ISfcl'J.O 11680.6 10723.9 9795.0 6811.2 7B36.7 6936.4 611 1.2 5346.8 
4643.6 3999.0 3409.6 2936.7 2295.7 .0 
10777.2 9551.4 8432.3 7896.2 73B5.5 6459.1 6342.0 5465.2 
4635.8 4234.0 3957.0 3648.0 335'6.7 2131.2 
.688 -702 .722 .736 .754 .778 .809 .845 
.998 1.071 1.161 1.286 1.463 .000 
MACH = .800, ALTITUDE == 10000., THRUSTS/FUEL FLOWS/SFCS/NOX 
17EE5.7 15556.3 13346.1 32.252.9 11191.6 10071.0 8954,1 7927,/ 
5305.7 4369.2 3695.7 3211.2 2623.0 .0 
12677.8 112:39.4 9919.4 9288,7 868.8 . C 8068.8 7460.4 6899.6 
5453.4 5039.5 4654.8 4291.4 39.51.1 2507. n 
.709 .723 .743 .753 .776 .801 .833 .670 
0>'l !,.••' 1 .195 1.324 1.506 . 000 
MACH = .800, ALl'ITUTE - 500.'. , THRUSTS/FUEL FLOWS/SFCS/NOM 
18913.5 16450.2 14113.1 11957.0 11834,8 106*9.7 9468.7 8383.2 5610.6 1631.8
 4119.6 3J27.5 2773.4 .0 13954.6
 12371.3 10918.4 10224.1 9562.9 B68.1 t 8211.7 7594.4 
fi 0 02 .6 5547,0 51-33.6 1723,6 4349.0 2759.5 
.73B .752 .774 .789 .80R .834 .557 .906 
1.070 l.iiS 1.241 1,37b 1.568 .000 
MACH = .800, ALTJ'J'JDE - 0., THRUSTS/FUEL FLOWS/SFCS/NOX 
19837.8 17254.1 14802.8 13590.3 12413.1 11170.2 4 8732.9 
5444.7 5067.9 4.320.9 3595.0 2909.3 .0 
11315.2 13577.5 1I9B2.9 11221.0 10495.4 9747,4 9012.4 8334.9 •'"187.8
 6087.9 5623.2 5134.1 4773.U 3028.6 
.772 .7*7 .810 .826 .846 .873 .907 .948 
1.119 1.21-1 1.301 1.442 1.641 .000 
MACH = .750, ALTITUDE » 400O0., THRUSTS/FUEL FLOWS/SFCS/NOX 
4941,1 4295.4 JhR6.8 3390.8 3103,S 2798.1 2493.4 2212.3 
1489.5 1286.7 1100.4 908.2 736.7 .0 
3006.4 2665.3 2331.4 2204.C 2062.9 1917.2 1775.8 1641.1 129B..2
 120D.O 3IDB-4 1020.7 939. 5j 592.0 
.60S .620 .636 .650 .665 .685 .711 .742 
.«72 .933 1.007 1,124 1.276 .000 
MACH - .730, ALTITUDE - 30000., THRU!TS/FUEL FLOWS/SFCS/NOX 
6290.5 5468.f 4693.7 4316.9 3951.1 3563.3 3174.4 2816.£ 
1B.H5.3 1638.2 1400.9 1155.2 937.9 .0 
3829,3 3395.3 2996,7 2807,7 2628.0 2442.3 2259.6 2090.6 
1653,3 1538.6 1*12.0 1300.3 1197.2 754.2 
.609 .621 .6:8 .650 .66:. .686 .712 .742 
.872 .933 l.OOd 1.125 1.276 .000 
MACH = .750, ALTITUDE = 30000., THRUSTS/FOE.L FLGWfc/SFCS/NOX 
7964.6 6923.9 3J42.9 5465,7 5O02,6 4510.4 4019.2 3565.2 
24DI.0 2174 1.773,7 14(13.9 1187.5 .0 4959.7
 4397.0 3880.8 3636.1 3403.3 3162.H 2320.3 2707.4 2141.7 13/9.6 1-128,6
 1683,9 Is: .4 976.7 
.623 .635 .653 .665 .670 .70] .728 .759 
. •• ' • ••')•! 1 331 1.150 1 .306 . 000 
MACH = .750, AL.?:T'JD3 = 2 5000,, THRUSTS/FUEL FLOWS / SFCS ,'NOX 
3978.0 8671.2 7445,1 6847.3 6267.2 5650.5 5035.2 4467.6 
3007.9 2598.4 2222.0 1831.9 1437,7 .0 
6355.7 5631.6 4973.1 4659.5 4361.2 4053.0 3749,9 3459.4 
2714.5 2516.4 2313.2 2157.9 1986.8 1U0I.5 
.637 ,650 .668 .690 .696 .717 .745 .777 
.932 .976 1.055 1.177 1.335 .000 
RATIOS 
5982 . 6 
6380 . J .
 J11 
RATIOS 
7383 .8 
7023 . 1 
. 951 
RATIOS 
7744 .7 
7707 . 9 
. 995 
115 .0 
. 938 
FOLLOW 
S109.1 
5999.5 
FOLLOW 
6160 .2 
6 4 93.6 
1 ,005 
FOLLOW 
6775 . 9 
7126.7 
1.Q53 
RAT [OS 
1951 .5 
FOLLOW 
17. .8 
MACH = .750, Al :T I TULlE = 20O00., THR1 'SIS/ FUH 
1238E.2 10769.4 9243.5 8501.3 7781.0 7015.5 
3734.S 3226.1 2756.S 2276.9 1B47.1 .0 ROTO.a
 715E.1 6311.1 5916.9 5536,1 5146.7 
3435.1 1221.4 2975.5 2710.2 2522.9 1589.3 
. EI.OWS/SFOS/lOOX 
6251.5 5546.8 
1518 .1 
. 778 
RATIOS 
1933 .9 
.778 
RATIOS 
1145 .7 
25D4 . 5 
. 796 
- YTIOS 
3940.9 
•20".4 
. 814 
RATIOH 
4892 . 9 
1404.0 
. 821 
;-;,OLLOK 
217 8.1 
1788.6 
. 821 
FOLLOW 
2757.7 
FOLLOW 
-•ou-ow 
42B9.3 ..4 37K9.2 
Nov 18 96 
15:09:06 C17-SHORT-FLOPS-OUT .65'. .664 .681
 -III .711 
.933 .995 1.079 1.203 1.366 .734 .000 
MACi i, AL' ' •; DC . , 'CJ l/KJJii. I . .'.-.'i/SFCS/NOX 
15203.4 13269.0 11388.9 10474.4 95B7.0 864J.7 7702.4 6834 2 
56*1.3 3974.H 3399.1 2BD5.4 2275.7 .0 
10169.0 SOIL.I 7956.8 74SS.1 6977.8 6464.7 5599.8 5551.0 •I,si,2
 1 54.a 3749.1 3452.6 3178 . t 2002.4 
666 ;I7S .699 .713 .728 .750 .779 ,812 
.954 1.021 1.101 1.231 1.397 .000 
MACH -: .750, ALTITUDE = 100OD., THRUSTS/ FUEL FLOWS/SFCS/NOX 
L8359.2 15960.2 1369b.t 12 •.•:'<( . 1- 11531.4 10396.8 9264.7 B220.3 
5534.5 4761.0 40S8.5 3374.4 2737.3 .0 
12S2S.0 11103.9 9B00.3 9132.3 8594.5 7987.2 7389.9 6837.1 
5408.5 4993.2 4617.7 4252.5 391.:.3 2466.4 
.542 .696 .715 .729 .713 .768 .798 .832 
.977 1.046 1.129 1.260 1.430 .000 
MACH = ,750, ALTITUDE = 5005,, THH(JSTS/FUEL FLOWS/SFCS/NOX 
19452.9 16911.0 14514.9 13349.5 1221B.4 11016.2 9315-6 8710,0 
•'•••'. 3 50-5 . 9 4 3 )2. j j.4 ,J900.4 .0 
137F4.7 12230.7 10785.9 10105.9 9458.9 8790.5 8133.1 7524.H 
3952.5 5502.0 5082.1 46OT-2 4309.1 2714.4 
.7-.19 .723 .743 .757 .774 .798 .829 .864 
l.o,; 1.01.6 1.173 1.309 1.486 .000 
HHZH = .750, ALTITUDE = 0., THRUSTS/FUEL FLOWS/SFCS/NOX 
20470.4 17795.5 15274.G 14047.7 12 357.5 11592.4 1C330.O 9365.6 6171.0
 5130,3 4558.7 3762.4 3052.1 .0 
151^7.S 13411.0 11836.6 11090.2 10380.2 96-16.7 8925.3 3257.7 
6532.3 0D37.3 5577.2 5136.0 .'?.. 3. J 2^73.8 
.739 ,734 .775 .739 .807 .832 .864 .901 
1.0:9 1.133 1.2J3 1.365 1.549 .OOO 
M^CH = .700, ALTITUDE - 35000,, THRUSTS/FUEL FLOWS/SFCS/NOX 
5165.7 5374,1 4G34.6 4275.4 3922.3 3542.8 3167.0 2&17,0 
1914.0 1665 6 1415.4 1174.2 955.5 ,0' 3628.4
 3217.6 .041.6 266..9 24L .2 1 ,.6 2144.0 1982.9 
1566.5 1447.0 1133.7 1227.2 LI 2 3.0 692.H 
.488 .599 .614 ,624 ,636 .654 .677 .704 
.•9.17 .869 .942 1.045 1.179 .000 
MACH = .700, ALTITUDE 30000., THRUSTS/FUEL FLOWS/SFCS/NOX 
7807.7 6804.1 5867.9 5413.0 4966.0 4485.6 4009,8 35*6.« 
5428.1 2103.8 17*2.0 I486.7 L 211.0 .0 
4698.3 4166.4 3613.3 1452.0 3230.9 3001.0 2776.2 2567.6 
2028.5 1673.7 1726.9 1589.0 1460.6 896.7 
.602 .612 .423 .638 .651 .669 .692 .720 
,835 ,889 .354 : .0I\<R 1.206 .000 
MACH - .700, ALTITUDE = 25000., THRUSTS/FUEL FLOWS/SFCS/NOX 
97*: .4 S'IAJ.: 7351.3 6/81.5 t/221.4 5611?. 5 5023 4 4168.2 
3041.3 2641.9 2245,0 1862.5 1517.1 .0 
6020.4 511B.9 471'.' 8 4423 5 <,"...0.l 38-15.5 3557.4 7>2?0.1 
J5S9.3 2401.0 2212.9 2D3S.2 1871.7 J149.C .615 .626 .642 .452 .663 . 6K4 .701! .736 .854 S09 .986 1,093 1 S14 .000 MACH = .700, ALTITUDE = 2U000., THRUSTS/FUEL FLOWS/SFCS/NOX 12.11.?. lf>! M .) » 1.-5.  8417.9 7722.7 6975. 5 623 3.6, 51,06.4 3776.  31.79.4 2786.3 231.1. .9 1KB3.2 0 7642.7 6777.5 5991.7 5515.4 52 55.8 tLMil.a 4516.0 4176.7 3299.7 2D4B.O 2809-i 2584.9 237S.O U5S-6: .529 .641 .65  .667 .681 ,700 ,724 .75;. .17  .329 1.005 1.118 1.262 .300 
RATIOS FQl. :,•'/> 
60/8 5 5284.9 
513 4.9 474 9.1 
,852 .899 
RATIOS FOLLJC™ 
7251.2 6356.8 
6324,6 5849.4 
.872 .920 
RATIOS FOLLOW 
768.3.2 6735.5 
6960.7 6437.7 
.906 .956 
RATIOS FOL1/ 
8085.0 T06F 
7638.7 7064.8 
.945 .997 
RATIOS FOLLOW 
::492.5 21*3.2 1E13.6 1695,0 .73  .773 
RATIOS FOLLOW 3155.8
 2776.8 
2374.2 2194.9 
.752 ,790 
RATIOS FOLLOW 
3353.6 3478.8 3042.3 2812.5 .770 .808 
RATIOS FOLLOW •i
 9 0 .'  6 4 316.2 
3 362.1 3 570.4 
,787 .927 
MACH = .700, ALTITUDE » 15000., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
14551.B 13032.5 11259.4 10368.4 9511.ft 3591.6 76*0.1 6*31.4 5044,6 511B.7 
4601.3 4039.2 3432.4 2347,5 2319.5 .0 
9625 , 3 8535.7 7546.0 707.2.2 6519,2 5148,2 5657.5 5250.2 4864.0 4496.6 
4155.7 3338,6 3538.0 3255.5 2992.4 1*137.0 
.644 .653 .671 .682 .696 .716 .741 ,770 ,805 ,845 
.39:1 .950 1.031 l.iOJ 1.290 .CUU 
MACH - .TOO, ALTITUDE = 10000., THRUSTS /FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
133R7.J ir.<Oli.5 13743.8 126/8.4 .1631 .3 10506.1 i'iSl.7 8553.7 7,:71.i 6503.8 
5687 .S 4911*.3 4197 ,2 3482.1 2836,3 .0 
IZULZ.L 10670.fa 9133.4 8841.0 8274.8 7685.9 7110.0 6575.9 60RO.fi 5621.3 
5195.1 4798.7 44 3.. 9 4069.7 374 0.1? 22i.6.5 
.658 .670 .666 .697 .711 .732 .757 .787 .823 .864 
.913 .972 1.054 1.163 1.319 .000 
MACH = .700, ALTITUDE = 5000., THRUSTS/FUF.L FLOWS/SETS/NOX HAT IO.-! FOLLOW 
20566.7 17437.3 15C51.2 13912.2 12763.2 11325.4 10305.6 9166.6 81JO.f! 7135.7 
6341.3 541S.9 460::,7 1EJ0.9 31 12.3 .0 
29,5 12065.6 106B5.2 10014.2 9372.8 8705.9 80=3.5 7448.5 6887.5 6367.2 
5SE4.5 5433.5 50-09.6 4 603.7 4237.3 26U1.2 
.679 ,709 .720 .734 .755 .781 .813 . S-,9 .892 
.943 1.O03 1.088 1.206 1 .3.61 .000 
MACk = .700, A;/.--. :-,r.;K = 0., THFtjSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
21196.2 18471.7 1593D.2 14695.3 13481.6 12177.4 10435.7 9682,6 136-7,4 7538.5 
6592.6 5725.0 4364.9 40J6.0 3237.5 -0 
14960.7 13267.1 11728.8 - 09PZ•3 n!2R8.3 9556.2 B840.1 8176.0 7560.2 6989.1 
6453.2 5966.4 5499.1 5060.0 4651.1 2455.3 
.705 .718 .73 5 .74? .763 .','65 .812 344 .ITLIZ .927 
. 9HD 1.042 1. .110 .' .254 1 .4L5 .000 
MACH = .600, AT.TITUP3 = 30000., T/4KUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
771B.9 67B0.6 589B.1 5443.6 5D1D.5 4535.4 4067.4 3629.5 3219.0 2341.2 
2494.1 2I2R.5 1782,4 1172.0 1196.9 .0 
4290.4 3812,0 3375.9 3J 54.9 2946.1 27361.2 2514.0 2317.2 21M.4 196V2 iaOE.
 1657.8 1517.4 1387.7 1263.6 750.4 
.556 .562 .572 .580 .j33 .601 .618 .638 .663 . b92 
.725 .779 .851 .943 1.060 .000 
MACH = .600, AI T I'J'UIJF, - 25000., TKHI: STB / FUEL FLANS/SFCS/NOX RATTOS FOLLOW 
9670.4 3494.8 T3S9_J 6S19.8 6277.1 5682.0 5095.7 4547.0 4D32.8 3559.5 
•:.'.4.7 «C66.!> 2233.0 1844 1 1499.1 .0 
5498.0 4884.9 4326.1 4041.9 3775.3 3493.5 3221.6 2969.3 2735.1 2518.4 
2317.3 2124.4 1944.5 1778.2 1625.6 961.6 
.-in" ,575 ,585 .593 .501 .615 .632 .653 .678 .708 
.742 .797 .871 .964 L.0"4 .000 
>'4ACH > .600, AM1 :.!•!.:•:•!•; = 20000., THRUSTS/FUTL FLOWS/SPCS/BOX RATIOS FOLLOW 
120O1.5 10542.5 91','0.5 8463.8 7790.3 7051.7 6324.1 5643.2 5005.0 4417.6 
33/7.9 3309.4 2771.3 2283.7 1851.0 .0 
6978. D SJ9S.9 5490.7 5]" 1.2 479 i. 5 4 434.0 43*F\.{L 3768.7 1471,5 1196.3 
2941.i 2696.2 2467.9 2256.5 2063.2 1220.4 
.581 .584 .599 .6M6 .615 .629 .647 .668 .694 .724 
,753 . :' : : .34 1 . '736 1.105 . 000 
MACH = 605, ALTITUDE = 15000., THRUSTS / FUEL f[/)WS / KJ-'L'S / NOX KATlil-S FOLLOW 
14773.5 12r77.5 1I2BB.5 I041B.6 95B9.6 B630.4 7734.7 5946.6 6163.0 5417.9 
4773.6 4073.S 3411.4 2817.3 2290.8 .0 
8782.4 7 303.1 6910.5 64 5B.1 603D.6 5530.6 5146.1 4743.2 43H9.0 4022.8 
3701.7 3393.5 3106.1 26J0.5 2596.7 1536.0 
.594 .£01 -L-±2 .620 .629 .643 .661 .683 .709 .740 
.775 .333 .911 1,008 i.L24 .000 
MACH * .600, ALTITUDE * 10000.. THRUSTS / FUEL FLOWS /SFCS/NOX RATIOS FOLLOW 
IR055.3 15(1(0.3 13796.2 12733,0 11719.9 1D6D4.7 9514.0 848?. 6 7519.* 6645.9 
5B34.0 4974.7 41E9.2 3443.1 2799.7 .0 
Nov 
15:09:06 C17-SHORT 
10971.8 9748.4 8633.3 8068.0 7533.9 6971.7 6429.0 5925.7 5458.2 5025.7 
4624.5 4239.4 3880.4 3548.6 3244.1 1918.9 
.608 .615 .626 .634 .643 .657 .676 .698 .725 .756 
.793 .852 .931 1.031 1.159 .000 
MACH = .600, ALTITUDE = 5000., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
21508.6 18893.9 16434.9 15168.4 13961.5 12637.8 11333.7 10113.4 8969.7 7917.0 
+ 6949.9 5931.0 4966.6 4101.7 3335.2 ,0 
13368.8 11878.0 10519.3 9830.6 9179.8 8494.8 7833.5 7220.2 6650.6 6123.6 
+• 5634.8 5165.6 4728.1 4323.9 3952.8 2338.2 
.622 .629 .640 .648 .658 ,672 .691 .714 .741 .773 
.811 .871 ,952 1.054 1.135 .000 
MACH = .600, ALTITUDE = 0., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
22932.0 20144.2 17522.5 16172.2 14885.4 13474.1 12083.7 10732.7 9563.3 8440.9 
*• 7409.8 6323.5 5295.3 4373.1 3555.9 .0 
14692.6 13054.2 11561.0 10804.0 10088.9 9336,0 8609.2 7935.2 7309.1 6730.0 
H- 6192.7 5677.1 5196.3 4752.0 4344.2 2569.7 
.641 .648 .660 .668 .67B .693 .712 .736 .764 .797 
+ .836 .898 .981 1.087 1.222 ,000 
MACH .500, ALTITUDE 20000., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
12279.6 10898.4 9607.3 8876.8 8171.1 7390.0 
4047.4 3447.9 2878.4 2371.0 1917.6 .0 
6523.6 5808.6 5156.8 4797.4 4456.8 4098.6 
2628.9 2391.2 2169.8 1967.0 1780.6 992.1 
.531 .533 .537 ,540 ,545 .555 
.650 .694 .754 .830 .929 .000 
6628.2 5922.0 5270.0 4669,2 
3756.5 3441.5 3151.4 2383.4 
MACH = .500, ALTITUDE = 15OO0., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
15110.5 13410.8 11822.1 10923.2 10054.8 9093.6 8156.2 7287.2 6484.9 5745,6 
* 4980.5 4242,8 3542,0 2917.6 2359.7 .0 
8207.6 7308.0 6488.0 6035.8 5607.3 5156.6 4726.2 4329.9 3964.9 3627.8 
* 3307.5 3008.4 2729.9 2474.8 2240.2 1248.2 
.543 .545 .549 .553 .558 .567 .579 .594 .611 .631 
+ .664 .709 .771 .848 .949 .000 
MACH .500, ALTITUDE 10000., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
18456.3 16380.3 14439.7 13341.9 12281,1 11107.1 
6083.2 5182.3 4326.2 3563.7 2882.2 .0 
10247.5 9124.4 8100.5 7535.9 7000.9 6438.2 
4129.6 3756.2 3408.3 3089.8 2797,0 1558.5 
.555 .557 .561 .565 .570 .580 
.679 .725 .788 .867 .970 .000 
9962.2 8900.8 7920.8 7017.8 
5900.8 5406.0 4950.3 4529,4 
.592 .607 .625 
MACH = .500, ALTITUDE = 5000., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
22387.6 19869.3 17515.5 16183.7 14897.1 13473.0 12084.2 10796.7 9608.0 8512.6 
+ 7379.0 6286.1 5247.7 4322.8 3496.1 .0 
12703.7 11311.4 10042.1 9342,2 8679.0 7981.4 7315,2 6701.8 6136.8 5615.1 
+ 5119.4 4656.5 4225.3 3830.5 3467.4 1932.0 
.567 .569 .573 .577 .583 .592 .605 .621 .639 .660 
+ .694 .741 .805 .886 .992 .000 
MACH = .500, ALTITUDE = 0., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
24956.3 22149.2 19525.2 18040.7 16606.4 15018.9 13470.7 12035.5 10710.5 9489.3 
t 8225.7 7007.4 5349.9 4818.8 3897.2 .0 
14480.5 12893.5 11446.7 10648.9 9892.9 9097.8 8338.4 7639.1 6995.1 6400.5 
* 5835.4 5307.8 4816.3 4366.2 3952.4 2202.2 
,530 .582 .586 .590 .596 .606 .619 .635 .653 .674 
* .709 .757 .823 .906 1.014 .000 
MACH = .400, ALTITUDE = 10000., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
19383.6 17374.6 15462.0 14297.1 13170.0 11919.3 10704.3 9577.1 8534.5 7486.4 
643S.2 5489.0 4620.9 3793.9 2974.1 .0 
9759.2 8703.1 7734.3 7157.0 6612.0 6040.5 5498.7 5001.8 4545.3 4117.7 
3717.1 3351.0 3014.8 2703.8 2397.4 1285.7 
.503 .501 .500 .501 .502 .507 .514 .522 .533 .550 
-OUT 
.577 .610 .652 .713 .806 .000 
MACH = .400, ALTITUDE = 5000., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
23508.6 21066.6 18747.6 17335.2 15968.6 14452.1 12978.9 11612.2 10348.0 9077.2 
7806.3 6655.4 5602.8 4600.0 3606.1 .0 
12093.9 10785.1 9584.6 8869.2 8193.8 7485.5 6814.2 6198.4 5632.7 5102.8 
4606.3 4152.6 3736,0 3350,6 2970.9 1593.3 
.514 .512 .511 .512 .513 .518 .525 .534 .544 .562 
.590 .624 .667 .728 .824 .000 
MACH = .400, ALTITUDE = 0.. THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
27293.1 24462.5 21769.7 20129.6 18542.7 16781.7 15071.1 13484.1 12016.1 10540.5 
9064.6 7728.2 6506.0 5341,5 4187.4 .0 
14316.7 12767.4 11346.2 10499.3 9699.7 8861.3 8066.6 7337.6 6668.0 6040.6 
5453.0 4915.9 4422.7 3966.5 3517.0 1886.1 
.524 ,522 .521 .522 .523 .528 .535 .544 .555 .573 
.602 ,636 .680 .743 ,840 .000 
MACH ~ ,300, ALTITUDE - 5000., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
25221.8 22780.4 20475.9 18952.7 17477.0 15844.1 14241.2 12748.9 11289.8 9828.3 
8497.4 7252.9 6113.1 5047.1 3865.9 ,0 
11717.0 10457.3 9303,6 8565,0 7869.8 7146.8 6460.9 5833.8 5253.4 4713.4 
4222.2 3772.6 3360.8 2978.2 2533.2 1290.2 
.465 .459 .454 .452 .450 .451 .454 .458 .465 .480 
,497 .519 .550 .590 .668 .000 
MACH = .300, ALTITUDE = 0., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
29925.9 27029.1 24294.9 22437.5 20736.6 18799.2 16897.3 15126.7 13395.4 11661.4 
10082.2 8617.5 7253.3 5988.4 4586.9 .0 
14181.3 12656.7 11260.3 10366.3 9524.9 8649.9 7819.7 7060.8 6358.3 5704.8 
5110.2 4566.0 4067.7 3604.6 3126.4 1561.6 
.474 .468 .463 .461 .459 .460 .463 .467 ,475 .489 
.507 .530 .561 .602 .682 .000 
MACH = .200, ALTITUDE = 5000., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
27500.8 25037.4 22681.3 20972.5 19316.9 17487.4 15698.9 14038.7 12320.6 10738.9 
9250.9 7887.4 6650.8 5293.1 3997.4 .0 
11508.8 10281.6 9152.3 3369.9 7636.9 6879.8 6166.8 5519.7 4917.3 4371.7 
3874.7 3423.4 3014.4 2597.6 2220.9 1058.6 
.418 .411 .404 .399 .395 .393 .393 .393 .399 .407 
.419 .434 .453 .491 .556 .000 
MACH = .200, ALTITUDE = 0., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
32951.1 29999.5 27176.4 25129.0 23145.3 20953.1 18810.2 16821.0 14762.4 12S67.2 
11084.3 9450.6 7968.9 6342.1 4789.7 .0 
14080.4 12579.0 11197.4 10240.1 9343.4 8417.1 7544.8 6753.1 6016.1 5348.6 
4740.5 4188.4 3687.9 3178.0 2717.1 1295.2 
.427 ,419 .412 .408 .404 .402 .401 .401 .408 .416 
.428 .443 .463 .501 .567 .000 
MACH = .100, ALTITUDE = 5000., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
30350.4 27786.1 25342.0 23469.4 21650.2 19624.5 17640.2 15716.2 13786.2 12025.3 
10391.6 8896.4 7409.2 5784.9 4429.6 .0 
11408.3 10192.8 9075.9 8258.4 7495.0 6707.9 5971.3 5299.8 4683,3 4130.5 
3629.4 3178.8 2750.0 2330,0 1968.8 912.7 
.376 .367 .35B .352 .346 .342 ,339 .337 .340 ,343 
,349 .3S7 .371 .403 .444 .000 
MACH = .100, ALTITUDE = 0., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
36489.0 33406.0 30467.6 28216.2 26029.1 23593.7 21208.0 18894.9 16574.5 14457.5 
12493.4 10695.7 8907.8 6954.9 5325.6 .0 
14016.5 12523.1 11150.9 10146.4 9208.5 8241.5 7336.4 6511,4 5754.0 5074.8 
4459.1 3905.5 3378.8 2862,7 2418.9 1121.3 
.384 .375 .366 .360 .354 .349 .346 .345 .347 .351 
.357 .365 .379 .412 .454 .000 
MACH = 000, ALTITUDE = 5000., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
Nov 1896 
C17-SHORT-FLOPS-OUT 
13S24.6 31141.5 2B571.=> 26*69 1 24422.6 22105.5 19B79.3 17675.0 15512:.9 
* 11702.1 10019.1 B071.S $34,2,6 4893.$ .0 
11J77.9 10146.3 S052.A 8136.1 7180.5 6545.0 577S.4 5081.5 4452.1 
+ 33- >.8 2 IL^A. 0 2465-9 2055.1 1721.0 910.2 
.236 ,126 ,.317 .309 . J 02 .296 .291 .288 .287 
+ ,2S3 .292 .305 ,326 .352 .000 
MACH - .000, ALTITUDE = 0., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS 
46700.0 37471.4 34379.6 3)8-48.5 29386.8 26598.8 23920.0 21267.7 13666.1 
• 140-30 B 12055,6 9712.5 7613.9 5R37.5 .0 
13995.6 12505.9 11135,6 10069.4 907B.6 8050.8 7109.0 t*S3 .1 5476.4 
T 4161.0 3(01.6 3033,2 2540.3 2118.0 1113.7 
.344 .334 .324 .316 .309 .303 .297 .294 .293 
: -
JEAB.9 
.287 
FOLLOW 
16285,S 
4783.6 
.294 
. 29b . 299 .312 .333 . 360 
# REVISED PROPULSION SYSTEM DATA 
BASELINE ENGINE THRUST THRSO •.••Ay;-:; .: ; yr.-:~ .
r w NG BASELINE INLET WEIGHT WIN;, 
BASELINE NOZZLE WEIGHT WNOE 
BASELINE NACELLE LENGTH XNAC 
PASEL'NF NACELLE DIAMETER DNAC 
.000 
40700.D 
7100.0 
.0 
.( 
12 . 2j 
6 .23 
LBF 
LBF 
i.3F 
LBF 
# NAME!IST SMISSIN 
PERFORMANf*>: CONTROLS AND FACTORS AND MISSION EEOMENT DEFINITION 
VALUE DI MENS I ONO DESCF.I PT'JON NAME 
ENDURANCE MISSION SWITCH IN::R 
OVERALL FUEL FLOW FACTOR FACT 
CDO FACTOR FCDC 
CDI FACTOR FCDI 
5UB50NIC CO FACTOR FCDSUB 
SUPERSONIC CD FACTOR FCCSUP 
fcifl^RNE SCALING SWITCH ISKAL 
OWE FACTOR OWFACT 
PRINT FLAG I FLAG 
0PTA1LED MISSION PRINT MSUMPT 
TEMPERATURE DEVIATION DTC 
TALC RAMP WT OR RANGE IRW 
RAMGE TOLERANCE HTDL 
ATA TRAFFIC ALLOWANCE I ATA 
WEIGHT INCREMENT DWT 
0 
OOOO 
OOOO 
OOOO 
GROUND OPERATIONS AND TAKEOFF INPUT 
TRXFOJ/F TIME TAKOTM 
TAXI-OUT TIME TAX01W 
APPROACH TIME APPRTM 
A 'ROACH FL FLOW FACTOR APPFFF 
TAXI-IS TIME TAXITH 
1 .C0OC 
1.000C 
1 
1.000C 
2 
1 
.0 
1 
.0010 
0 
1. 
2 .0 
15 . 0 
.0 
2 . 00 
2.0 
KIN 
KIN 
MIN 
MIN 
iAKEOFE MOWER SETTING ITTFF 1 
TAXI FUEL FLOWS W3LL BE FROK THE ENGINE DECK 
IN. JT FOR : CL -.. r'.'HE. '".E:-
MINIMUM CLTNS MACH NUMsER CLMMIN 
MAXIMUM CLIHF3 MACH NUK5ER CLMMAX 
MINIMUM CLIMB ALTITUDE CLAMIN 
FT 
MAXIMUM CLIMB ALTITUDE CLAMAX 
FT 
NUKB-ER DP CLIMB STEPS NINCL 
CLIMB OPTIMIZATION FACTOR FWF 
FOLLOWING CRUISE SEGMENT NCRCL 
(1 
.3000 
. 0000 
0. 
(2! 
.3000 
.0000 
0 . 
0 . 
(3) 
-3000 
. 00DD 
0. 
0. 
" • 
. D010 
1 
{4 1 
.0000 
0 . 
31 
0 
DRAG COEFFICIENT INCREMENT CLDCD .0000D .ooooo . DOOOO .00000 
MO OF POWER 6ETTINCS I PRCL 1 1 1 1 
STORE DRAG DURING CL 1 KB ISTi.'L 0 0 0 0 
MAX CLIMB POWER SETTING MAXCI, 1 
FAA CL1KH ENFOHCEB IFAACL 0 
FAA DESCENT ENFORCED 1 PAADE 0 
MINIMUM CLIMB RATE SWITCH NODIVE 0 
MINIMUM GLIMS RATE DIVLIM 0. FT/MIN 
Q LIMIT IN CLIMB Ol ' 1 . 0 PSF 
MAXIMUM RATS OF DESCENT RDL1M -99999.0 F'F/jilN 
IHUT 1 CRUiSE SCK?IVJLES AT (2) (3! 14) 
[51 (6J 
CRUISE OPTION SWITCH IOC 2 1 1 1 
1 1 
CRUISE OPT FUEL FACTOR FFU'EL 1 .000 1 .0.10 1 . 000 1.000 
1.000 1.000 
CRUISE OPT NOX FACTOR FNOX .000 .000 .000 .000 
. ODO .000 
MAXIMUM MACH NUMREIR CRHACH .7500 .0000 .0000 . OOOO 
.00DO .0000 
MAX"-MUM ALTITUDE CRALT 28000 -1. -1 . -1. 
-1 . -1. FT 
DRAG COEFFICIENT INCREMENT OI-aXH:I .00000 . OOOOO .00000 .OOOOC 
.00000 .00000 
STORE DRAG DURING CRUISE 1STCR 0 0 0 0 
0 0 
LONG ttflJSGE CRUISE FACTOR FLRCR 1.000 1.000 1 . 000 1.000 
1.000 1.000 
MINT Ml.*! MAOH NIlHHEH r.. 3000 .0000 .( • • .•OSO 
.0000 .0000 
MAXIMUM LIFT COEFFICIENT CRCLMX .0000 .0000 . OOOO . OOOO 
.0000 -OOOO 
ENGINE FEATHERING ALLOWED IFEATH 0 0 0 0 
ENGIEE FRACTION REMAINING .5000 . 5000 .5000 . 5 000 
.5000 5000 
I'DEFTH .OOOOC . OOOOO . OOOOO .000OO 
. OMUO .00000 
MTNJH-IJM CRUISJ3 ALTITUDE HPMIN 1000. 1000 . I-JOC . 10 00 . 
1000. 1000. FT 
INCREMENT IN CRUISE WT. DCWT 10 LBF 
.-.ATE OF CL.LHH f'ElLING 
KC III 100. Q FT/MIN INPUT ]-'-.-. DESCENT SCHEDULE DESCENT OPTION SWITCH 
DESCENT LIFT COEFF. 
MINIMUM DESCENT MACH NO. 
MAXIMUM DESCENT MACH NO. 
MINIMUM DESCENT ALTITUDE 
MAXIMUM DESCENT ALTITUDE 
NUMBER OF DESCENT STEPS 
DRAG COEFFICIENT INCREMENT 
STSBE DRAG DURING DESCENT 
RESERVE SEGMENT INPUT 
RESERVE CALC. OR CONST 
RESERVE FUEL 
FRACTION OF TRIP FUEL 
MISSED APPROACH TIME 
RANGE TO ALTERNATE AIRPORT 
RESERVE CL I.NS SCHEDULE 
RESERVE CRUISE SCHEDULE 
START RESERVE MACK NUMBER 
ENL RESERVE MACH NUMBER 
START RESERVE ALTITUDE 
ENU RESERVE ALTITUDE 
IVS 
DECL 
DEMHIN 
DFNHAX 
DEAMIN 
DEAMAX 
NINDE 
DEDCD 
TS7DE 
' 
RESRFU 
RESTRP 
TIMMAP 
ALTRAN 
NCLEES 
NCRRES 
SREMCH 
.-KK :•:•:' 
S P. EALT 
EKEALT 
FT 
FT 
1 
, 800D 
.3000 
. 000D 
0. 
0. 
31 
.00000 
0 
.000 LBM 
.000 7.0
 WIN 
50O. 0 N MI 
1 
1 
.3000 
. 3000 
0. 
0. 
FT 
FT 
C17-SHORT-FLOPS-OUT 
RESERVE HOLDING TIHE HOLDTM . 0 MIN I5D00. -.00310 -.00281 -.00262 -.0024B -.0C23" -.00228 -.00225 -.00223 
HOLD CRUISE SCHEDULE NCR.HOL 1 * - .00221 -.00219 -.00217 
HOLP POSITION SWITCH OHCPOS 1 20DDO. -.00272 -.00246 -.00210 -.O0S1B -.00208 -.00199 -.in' .00196 
CRUISE ONLY SWITCH ! CREW 0 + - . 0019$ - .00192 -.O0190 
2ND RES HOLD TIME OR PRAC THOLL 000 NIK 25000. •.00231 -.00200 -.00195 -.00.185 -.OCl'.'o -.00169 -.00167 -.00166 
'"HI • I CROIR: .'"OHEPULE NORTH 1 -. • : " -.COI63 -.00161 
30000. -.00187 -.00169 -.00150. -.00149 -.00142 - .00J.37 -.00135 -.n >; 
- .00133 .0C13I -.00130 
3C •'. -.OQ140 -.00126 -.00117 1) 111 - .00106 - . 00101 - . 00', NO -.ooioo 
MISSION SEQUENCE DEFINITION .0009O -.00097 
-.00074 -.U0U6J -.00062 -.00059 -.00056 - .00054 -.00053 -.00053 
STA :T nAch NUMBER 30CO ALTITUDE - 0. FT + - .00052 -.00052 -,00051 
CLIM1 USE CLIHE SCHEDULE (5000. .OOOOC .0ODD0 .ooooo . OOOOO: .00000 . ooooo .00000 .OCOD'J 
CRUISE USE CRUISE sc: ;EDUL:-: END CRUISE DISTANCE - 200 0 0 N Ml + .00000 .0Q0DO .ooooo 
,.F! OA ! PAYLOAT WEIGHT = 124UOO.0 LB 50000. .00079 .0O071 .0O066 .00062 .00059 .00057 .00056 .00056 
REFUEL . . AL' :- • -2000.0 LB TIME REQUIRED •- 105 . 0 MIN .00055 .O0DE4 . 00D54 
CRUISE USE CRUISE SCHEDULE 1 END CRUJSt UISTANCE 500 0 N MI 5:000. .0O152 .00146 .00135 .00128 .00122 .00116 .00110 .00.14 
DESCENT .00113 .00112 00111 
BUT! MACH NUMBER = .3000 ALTITUDE - 0 . FT 60000. .00251 .00226 .00209 .D0197 .00188 .00180 .00178 .00176 
+ - 00175 .00173 .00171 
#TITLE, BEOTN OUTPUT OF RESULTS 
C17 lire rt: Mission 
FIHAL ANALYSIS 
# AERODYNAMIC DATA 
POUCH NUMBER 
. 75 
COMPONENT 
+ CDF 
Hi NO 
* 42 .00533 
HORIZONTAL TAIL 
^ i5 .00156 
VERTICAL TAIL 
<• 48 .00074 
FUSULAGFL 
* r-.i .00477 
NACELLE 
* 67 .00040 
NACELLE 
+ 67 .0004C 
NACELLE 
l 67 .00040 
NACELLE 
+ 5 ? .000-10 
MISCEI.IJU'iEOUS 
+ .00084 
TOI'Al, 
+ 27 .01484 
ALTITUDE 
45000. FT 
REFERENCE AREA 
3BO0.00 SQ FT 
TECHNOLOGY LEVEL 
1 .20 
SQ FT 
5819.15 
1.7 17.80 
806.95 
8036.68 
Oil .34 
213.34 
213.34 
2 13 .34 
FT 
23.25 
13.00 
19.88 
159.10 
12 .23 
12 .23 
12 .23 
.0.23 
RAT1 TO 
, 1210 
. 0850 
. 1100 
7 . 2220 
1.9631 
1.9631 
1 .9631 
i .5631 
FACTOR 
1 ,440 
1 .305 
1 .396 
1 .233 
2.663 
2 . 663 
2 . 663 
2 . 663 
M : 1.3 IONS 
26 . 3 
14.7 
22 . 5 
179 . 9 
13 . 8 
13 . 8 
13 . 8 
13 . 8 
CHMK3S IN DHAG COEFFICIENT FROM CRUISE ALTTTTOF 
3D8 KALT-I NUHE-EL". 
500 .600 .200 . 300 
+ .773 .800 . 825 
0. - . 00409 -.00372 
+ - .302SJ -.00291 - . OO.: 
5000. -.00378 -.00344 
* -.00271 -.00269 -.00266 
1oooo. -.0U34 -.00313 
+ -.DD247 -.00245 -.002 4 
.400 
-.00347 -.00329 
-.00331 -.00304 
.00292 -.00277 
- . "0 '.I 5 
-.00290 
. OO.;. !0 
. 7 U 0 
. 00279 
, 00254 
.725 
.002 99 
• .002 76 
• .00232 
CF 
.002 
.002 
.002 
.001 
.002 
. ^ 0 2 
.002 
. 002 
. 003 
,750 
. 00296 
. 00274 
. 00249 
MACH 
. 500 
.200 
03416 
.300 
032 8. 
/I00 
03197 
. SCO 
03127 
, 600 
03104 
.7110 
03113 
.725 
03127 
.750 
00 .74 
.775 
03399 
. 825 
,050 
. 550 
.019152 
,03832 
.03852 
.03702 
.01763 
.03613 
.01693 
.03543 
.01670 
.03520 
,01692 
.03531 
.01706 
.03 544 
.01742 
. 036 19 
.01816 
. 038K2 
.01930 
. 04331 
.03497 
. 06529 
POLARS 
.100 
.600 
.0)964 
.04314 
.0 >4 
.0^ .4 
.01769 
.04095 
. 01696 
. 04026 
.01673 
, 01003 
.01686 
. 04012 
. 1. 17 
.04022 
.01724 
.04098 
.01782 
.04 • 9 
.01925 
,04903 
,03355 
.07117 
A] 
.350 
. 550 
,02027 
04642 
.01897 
04713 
.01806 
04624 
.01739 
04554 
.01716 
04531 
.01725 
04540 
.01736 
04S47 
.01759 
04604 
.01811 
04920 
.01947 
05470 
.03337 
07735 
UE - 45008. FT 
.200 
.7'0O 
.02111 
. 05527 
. 01981 
. 05397 
.0IB92 
.05308 
. 01E22 
.( 238 
.01799 
.05215 
.01811 
.05223 
.01622 
.05221 
.D1B47 
.05261 
.01902 
. 05545 
.02046 
.06092 
.03 447 
. 0R.168 
DESIGN MACH NUMBER, • 
MACH 
.200 
. 300 
. 40C 
. 50C 
.600 
.700 
.725 
.750 
.775 
.800 
82 5 
CL 
. 050 
. 771, 
CDF 
1ESIGN CL 
.01906 
.01776 
.01687 
.0161B 
.01559 
,01503 
,01490 
. 01184 
.01473 
.01461 
.01449 
CD I 
.00011 
.250 
.750 
.02235 
06357 
.02305 
0622B 
.02016 
06119 
.Ol?47 
06069 
.01923 
06046 
.01942 
06054 
,01955 
06058 
.01987 
U6U63 
156 
OO. • 
.02J22 
06746 
.03 663 
09009 
. 458 
CDC 
. 00000 
. OUODC 
. ooooo 
. ooooc 
.00035 
. 00097 
.00119 
.00155 
.00217 
.00353 
.01755 
.3 00 
. 02390 
.02261 
.02172 
02102 
020BO 
, 02101 
.02116 
.02152 
.0222 3 
.02417 
.03990 
.3 50 
. O2 077 
. 02117 
.02359 
.02290 
.02368 
02291 
02307 
.02341 
, 02'70 
. 02627 
. 04368 
.4 00 
.02781 
.02651 
. 02563 
. 02496 
. 02477 
.02499 
.02517 
.02555 
.( • -10 
.U292G 
.0485:1 
1,051 
. 99f 
. 919 
.831 
.74 1 
. 5-40 
. 601 
.565 
.536 
.46 
.400 
. 450 
.03068 
.02939 
.O2B50 
.02731 
.02760 
.02772 
.027BE 
.02B2H 
.02963 
.CO 0 3 i: 
.O530B 
C17-SHORT-FLOPS-OUT 
100 00014 3Z0DDO- 2BO00. 30196. 21054. 11662. .6964 .7500 445 1 .0301 
150 00099 4 1 1332.3 .3104 1J 20 . .0 .00 
2<JC .00177 316DOO. 28000. J01b6. 21649. 11956. . 6903 , 753:, 445 ' • ? 
250 00276 4 1 1155.3 .3259 15 5 2 4 . 0 .00 
300 .003 98 352020. 23000. 30496. 22270 . 15266. , SB55 .7500 445 9 .0232 
350 . 00542 4 1 .3415 15 81 1 U .00 
400 .00707 165O0O. 23000. 30496. 22914. 5533 . . 6805 .7500 445 9 .0235 
450 .0089!; 4 9 930-3 .3570 16 06 4 0 .00 
-™ 01105 3K4O0Q. 28000. 30496. 2358 1. 15932. . 6756 .7500 445 9 .0279 550 . D1337 4 9 813 . 2 .3725 16 23 
4 0 .03 
£00 . J.• -2 400000. 23000. 3D496. 24270. 16284 . .6709 . 75O0 445 9 .0272 
• 50 01868 •! 3 702 .8 . - J 16 48 £ 0 .00 
700 .02166 416DDD. 28000. 30496. 24998. 6661 . .6663 .7703 445 9 . 0267 
7 50 . 248 • 4 6 S96.5 
4320OD. 
.1035 
.» 
16 64 
30496. 
4 0 
25820. 
.00 
17. . . 6618 .7S00 445 9 .0260 
•••BBSSURE DRAG COEFFICIENTS.. CDP 4 9 488 .7 .4191 16 73 4 0 . 00 
MACH CL 448000. 2 6000. 30496. 26703. 17552. . 6573 .7500 445 9 .0254 
. S50 .100 . 150 .200 .250 .300 .350 .400 .450 4 0 332.3 .43 1 16 7 8 4 0 .03 
+ . 500 .550 . 600 .650 .700 .750 461500. 23O0O. 30496. 27646. 13351. . 3530 . 7500 445 9 .0247 
.ZOO .00055 .DD034 . 002 1 .00028 . 00OLJ3 .00067 0313 0 .00168 .00267 . 4 0 . N.: .4501 16 78 4 0 00 
+ 00404 00188 00616 .01069 01154 01965 480000. 28D00. 30496. 28674. 13599. .6487 . 7500 445 9 .0239 
.300 .00065 . '0034 .00021 14* .00053 .00087 0013O .00168 .00267 . 4 7 171.4 . 4656 16 74 0 . 00 
+ :0-'. 00553 0DB16 .01069 01454 01965 196000. 27779. I'.UBOl . 29708, 19203. . 6464 .7500 446 3 .0232 
.400 HOC 6! .00034 .00021 .00028 .00053 .00087 00130 .00169 .00267 4 4 100. 0 .4764 .1 3 70 4 0 .00 
+ 00404 00533 00B16 .01069 01454 01965 512000. 27100. 31757. 30627. 19B57. .6483 .7 553 447 6 . 0225 
.500 .00065 .00034 .00021 .00028 .00053 .00087 0017 i .00171 .00268 . 4 4 100.0 ,4772 16 7 2 4 0 .00 
+ 004 1 00538 00516 .01069 01454 01965 523:100 . 26123. 32704. 31542. 20507, .6502 .7500 44S 8 .0218 
.600 .00064 .00034 .00021 .OUL " .00052 .0008B 00131 .00175 .00270 . + S 100. 0 . 477 S 16 7 4 4 0 .00 
4 00404 005>JB DOS IT .01059 01454 01965 54 4000. 25751. 33645. 32452. 21154. . 6519 .7500 3 5 3 1 .0212 
.700 .00076 .00037 00022 .00030 .00051 .33099 ODI45 .00187 .00273 4 100.0 .4778 16 76 4 0 00 
+ 00404 005 9 908 16 .O.OSE oi • S 01 IbJ 560000. 25062 . :• i-8i. 3335S. 21758. . 6535 .7500 451 4 .0207 
.725 .000BD .00033 .00021 .00030 .00064 .00104 OOlllO .00195 .00275 4 1 100.0 .1777 16 79 4 0 .00 
+ 004il7 00592 00816 .3.1364 C144: 01957 57f00O. 2 :197 . 35S40. J42d3. 22472. . •. jJ5 .7500 452 5 .0201 
. TW) .00U52 .00041 .00021 .00032 .00073 .00116 00162 .00209 .00295 4 3 LOO.O . 4790 16 80 4 . 30 
4 004 10 00644 ( •: 9 .D1D97 01156 01933 592000. 23925. 36499. 35Z10, 23148. .5574 .7500 453 5 .0195 
. 77 5 .00116 .00043 . 00022 00r 6 .00091 .00141 00189 ,00249 .00398 . + 9 100.0 .4603 16 81 4 . 00 
4 00605 . 00355 0110E .01363 01699 02079 6030DD, 23355. 37453. 36133. 23822. .3593 .7500 454 6 , 0190 
. Soo .00151 .00062 .00029 .0OD5O .3""J.2 7 .00201 00267 .00403 .00332 4 B 100.0 . 4813 16 33 4 0 .00 
4 00873 01175 01493 ,01783 02107 02441 £24030. 22738. 33404. 37052. 24493. .6610 .7500 455 6 . 0186 
. B2 5 .002 62 .00106 .00033 . 00066 .002 02 ,00337 00622 .00947 .01248 . + 0 100 , 0 . 4321 16 34 4 0 .00 
4 01392 01987 02 L .02663 02997 03318 
4 5 
540000. 
100. 0 
656000. 
22221. 
. 4827 
21562. 
li 
39350. 
86 
40293. 
4 
37967. 
3 
38377. 
Z5150. 
.00 
25825. 
. 6627 
,6643 
.7500 
. 7500 
456 
457 
7 
7 
.0181 
,0177 
It CRUISE OPTIMIZATION RESULTS 4 2 100.0 .4331 1.6 ; • 4 a .00 
672000. 21ID2, ' 7- .). 39784. 26487. . 6658 . 7503 4^1 7 .0173 
4 2 100.0 . 4833 13 89 4 0 .00 
S'JHMAKV DATA FOR CRUISE SCHEDULE 1 
WEIGHT ALTITUDE THRUST FUEL SFC MACH VF.T.OCTTY SPEC1FI CRUISE SCHEDULE RANGE ANE TIME SUMMARY 
4 C RATE OF 1'L L/D ENGTNES NOX 
AVAILABLE RL'OUlftED FLOW NUMSER RANGE WEIGHT RANGE -1- TIMF 
4 3! MS OPERATING RATE (POIJKDS) (N.HI.I (HR) 
672000. ( . 05 
2080OO. 2 330 3. 30496. 17565. 12956. .7376 .7530 445 9 .0344 654C0U. 139 ! .33 
4 1 2657.1 .2313 11 84 4 • 0 00 656Q00. 280. 5 . 6 
2 2-1 OOC . 2BDDO. 30496. 17962. 13149. .7500 445 9 . 0339 643000. 423. 0 . 92 
, 1 2526 .5 .2173 12 17 4 . 0 00 *40QQO. 567. 3 1 . 24 
240DOO. 28550. 30196. 1R1J2, 13368. .7261 .•••330 445 9 . 0333 £32000. 713 4 1 . 56 
4 5 2273.4 .2373 13 03 4 . R, 00 624000. 8 61 3 1.S3 
256000. 28000. 7 196 . 18914. 13613. .7197 . 7500 445 9 ,0327 316000. 1011 1 2 .21 
4 5 2042 .8 .2483 13 53 4 . 0 00 6C80DO. 1 162 7 2.55 
272000. 25300. 30496. 19416. 13857. ,7137 .7500 445 9 .0321 €00030, 1315 4 2 - M 
4 B 1839 . 3 .2639 _4 31 4 . 0 DO 592050. 1472 1 j . 23 
2B8OO0. .:. 7vO. 33496. 19938. 14 11. . 7078 .'.3 70 445 9 . 3316 584050. 1629 9 3 . 5B 
4 0 1655 .3 .27" • 14 44 4 . 0 00 576000. 1789. 9 3-93 
3,54000 . 2 '•:. ., . 30496. 20483. 113BD. .7021 .7500 445 9 .35-71 538 5 • !!•• 2 . 4.-9 
t 1 14 , .T. .2949 14 34 < . Q UU 560000. 2113. 6 4 . 35 
CI7-SH0RT-FL0PS-0UT 
152000. 2233.3 5 .02 293QDD. 0. 44 .2 3993 7 353 .3 11187 I : 
CO 1634 .-ii 
544000. 2152.4 5 4 18682. 2E91IB . "51 1 2BD00. 113 . 9 
535000. 2523.3 j 7S 304000. 0 . 47 .4 4277 6 354 j 11269 1 98 3 1656 .3 
525000. 2797.7 3 17 + 39070. 284930 .7590 28500. 445.9 
520000. 2974.0 6 56 330DD0. _'. 50 .7 457C 8 350 . 6 11159 3 98 7 1673 .9 
312000. 3153 . < 93 4 1S470. 300530 .7500 280O0. 44^ . ^ 
501000. 3334.7 1 D 336500. 0 . 5 4 .2 4875 9 346 .8 11-150 . 8 ! • 0 ] 3 5 3 . 2 
496005. 3519.2 7 ' + 196B1. 316119 . 750C 28000. 445 .9 
45300:-. 3705.6 2D 352000. o. 57 .9 ^194 9 342 .9 11513 . 0 99 2 1700 . 9 
480000. 3895.9 3 62 4 20305. 3 31695 7500 28000. 4 4 5 . 9 
472000. 409O.1 9 06 61700. 0. 61 .8 5527 6 138 3 11636 . J 99 4 17 1 1 0 
461DOO. 42E6.2 5 50 4 20742. 3 472 53 .7500 24000. •445 , 
45S00O, 4445.I 9 94 3B40O0. 0. 65 .8 587 6 7 7 4 6 11730 .3 99 6 1721 .2 
41B0O0. 16863 9 0 4 * 21194. 362306 .7500 28000. 445 . 9 
140000. 1B91.5 ID IOOOOO. 0. TO 1 6243 0 330 2 1IB21 3 99 6 1728 . 6 
132000. 5098.9 11 32 4 21660. 378340 7500 28000. 445 .9 
424000. 5303.9 11 79 416000. 0 . 74 8 6630 7 325 6 1] 9 09 .6 99 6 1735 .3 
416000. 5521 . 7 12 37 4 23142. 393858 .7500 28000. 445.7 
4OBOO0. 4737 .0 12 V5 432000. 0 . 79 8 7044 0 320 5 11594 . 6 99 6 1741 . fi 
IOOOOO. 5954.8 13 21 4 22*46. 409354 . 7500 28000. 445.9 
392000. 6175.D : 3 73 448000. 0 . 65 4 74B7 4 315 0 120=13 . C 99 6 1717 •• 
1 R4 000. 6397.7 14 2 4 23184. 424B16 .75D0 23000. .! .1 5 . 9 
376000. 6422.8 : 4 7 4 4;. 4 000 . 0. Jl .6 7971 0 308 8 12160 . 5 99 E 1753 .6 
364000. 6550.3 15 25 + 2375J. 440249 . 7 50'7 2SOO0. 445 . J 
360090. 7080.3 1 ; 7C 480000. 0, 9 3 .7 8505 0 301 9 12217 .7 99 5 ! 75 3 .7 
352C00. 7311 .7 16 29 + 24348. 455652 mod 28000. 445 .9 
344000. 7547.5 16 .81 496030. 0. 105 .8 9054 1 294 9 12/ • / . 6 99 4 1763 .2 
334000. 77R4.8 17 3* 4 21971. 471029 .7500 27779. 446 .3 
3: 1000. a024.5 17 66 512000. 0, 105 3 9471 4 291 1 12502 .3 98 9 1764 . 9 
320000. .. r; IA 42 + 25605. 486395 .7500 27100. 117.3 
312000. 8511.0 ia 97 52B0OO. o. 110 5 9714 0 291 7 1233 : 97 8 ; 7 5 7 '.: 
304000. i 19 53 4 26241. 501759 . 7500 26423. 448 . 3 
29iH0p. 9007.1 20 09 1-id00. o. 110 4 9922 4 293 6 13359 a 96 0 1718 2 
233000. 925B.7 20 65 4 26896. 517104 .7500 25751. 450.1 
200000. 9512.6 21 22 56OOOO. o. ! 10 3 10330 t 1 J 5 13818 5 94 2 17 3.6 5 
272QDD. 37 6° . a ii 79 4 2T552. 532443 .75D0 25032. 451 . 4 
261UD0. 1O027.4 ri 37 57SC00. 0. 110 3 103 51 f 297 2 14274 .3 92 5 1723 9 
2560DO. I02RR.2 >.?. £6 4 26216 . 517734 .7500 24497. 452 .5 
216000. 10551.5 21 5:" 592000. 0. 110 .8 10604 2 293 5 14724 .9 90 8 1710 8 
2400O0. 10617.1 24 14 4 26906. 563094 .7500 27726. 453 . 5 
2.:: . 11085.0 24 75 604000. . 111 5 10479 7 299 3 15161 .8 89 2 1700 6 
.24" 1 11355.1 35 33 4 29608. 578392 .7! 10 23355. 454 . 6 
2 Iii 000. 11*27.4 ^5 96 624000. 0. 112 2 113.60 6 3 00 1 15600 8 87 1 1339 . 4 
2DBOOO. 11901.7 26 5 + 35321. 593679 , 7500 227BB. 455.6 
54DO0Q. H 2 8 11 J IS 1 2 3 01 0 16042 1 B6 2 1677 .9 
4 31047. 608953 .7500 22224. 156 . 7 ESEF.VE S JMMARY 4 [56000. 31797. 624203 0. Iii: .7500 5 11783 22662 . a 301 457 . 7 7 16475 2 34 7 1666 3 
.ISSED AP S-ROACH FUEL = 11 64. LB. E72 000. 
32583. 639417 
0. 114 
.7 500 
4 12163 
21::. 32 . 
2 302 
458 .7 
4 16900 0 83 2 1653 3 
START 
RESERVE 
RESERV: 
FUEL 
21 • ). 
1704 9. 
i ,u . 
240000. 
17575. 
:-56 oo. 
17933. 
-. 00 . 
IAI06. 
HO; 
END 
FUEL 
CL3HH CLIMB 
FUEL 
CRUISE 
DIET 
•r - • RVE M.,V 
HfcXtBtT NUMBER ALTITUDE VELOCITY 
0. 29.3 2704.9 376,0 
190951. .7^00 28000. 445.9 
0. 32.1 2950.7 372.6 
206762. .7500 . 3030. 445.9 
0. 35-0 3199.0 369.1 
222425. .7500 23000. 445.9 
0. 33.0 3455,3 103.6 
;=•>-*:>*.'. .7533 2 6 OOC . 44 5.9 
0. 41.D 3720.2 36J.S 
253o94. 7500 2UO00. 445.9 
CRUISE 
FUEL 
10967.2 
10890.7 
10954.7 
11033.1 
11111.6 
DESCENT 
DIST POE1. 
ITERATION 
ITERATION 
* ITERATION 3 --
RANGE = 
RANCF = 
RANGE = 
94 .7 
95.3 
95.9 
96.4 
97 .1 
1506.5 
1531.0 
1555.2 
157B.5 
ITF N 
ITERATION - RANGE = 
* ITERATION 6 -- RANGE = 
7074.944 
2723.241 
2462.925 
2500.233 
2499.998 
2500.000 
# OUTPUT FROM THE WEIGHTS MQD03.E 
I DESCRIPTION 
FOR GR0S3 WLIGHT = 
FOR SROSS WEIGHT = 
•OR CROS3 WEIGH'" ••• 
FOR GROSS WEIGHT = 
FOR GROSS WEIGHT = 
VALUE DIMENSIONS 
650000.00 
457591.AC 
447B2B-56 
4493:3.}. 58 
44322 • *>! 
449224.83 
Nov 18 96 
CALCULATED WING AREA 
CALCULATED ASPECT RATIO 
WING BENDING FACTOR 
ENGINE INERTIA RELIEF FACTOR 
WING WEIGHT BREAKDOWN 
TERM 1 
TERM 2 
TERM 3 
WING SPAN 
WING GLOVE AREA 
HORIZONTAL TAIL AREA 
MODIFIED VOLUME COEFFICIENT 
VERTICAL TAIL AREA 
MODIFIED VOLUME COEFFICIENT 
NACELLE LENGTH 
NACELLE DIAMETER 
LENGTH OF MAIN GEAR 
LENGTH OF NOSE GEAR 
MAXIMUM LANDING WEIGHT 
WING FUEL CAPACITY 
FUSELAGE FUEL CAPACITY 
AUXILIARY TANK CAPACITY 
TOTAL FUEL CAPACITY 
1 MASS AND BALANCE SUMMARY 
T LREF HORI CG-INCHES 
WING 
.0 .0 
HORIZONTAL TAIL 
.0 .0 
VERTICAL TAIL 
.0 ,0 
VERTICAL FIN 
,0 .0 
FUSELAGE 
.0 .0 
LANDING GEAR 
.0 .0 
NACELLE {AIR INDUCTION) 
,0 .0 
STRUCTURE TOTAL 
.0) ( .0) 
ENGINES 
.0 .0 
THRUST REVERSERS 
.0 73.4 
MISCELLANEOUS SYSTEMS 
,0 .0 
FUEL SYSTEM-TANKS AND PLUMBING 
.0 .0 
PROPULSION TOTAL 
.0) ( .0) 
SURFACE CONTROLS 
.0 .0 
AUXILIARY POWER 
,0 .0 
INSTRUMENTS 
.0 .0 
3846.0 SQ FT 
7 . 28618 
9 .2021 
, 919555 
12793.0 LB 
18515.1 LB 
7829.7 LB 
167.40 FT 
-92.05 SQ FT 
345.00 SQ FT 
1.539989 
395.07 SQ FT 
.100000 
12.23 FT 
6.23 FT 
41.91 IN 
29.33 IN 
364995.2 LB 
182720.0 LB 
.0 LB 
.0 LB 
182720.0 LB 
PERCENT WSEF 
-8 . 71 
.67 
.28 
.22 
14.29 
2.74 
.77 
( 27.70) 
6.32 
. 00 
,21 
.44 
I 6.98) 
. 99 
, 14 
.20 
C17-S HORT-FLOPS -OUT 
POUNDS 
39138. 
3024 . 
1279 . 
1000 . 
64181. 
12312. 
3478, 
i 124413.) 
28400. 
0 . 
959 . 
1984. 
( 31343.) 
4431. 
616, 
913 . 
HYDRAULICS 
.0 .0 
ELECTRICAL 
.0 .0 
AVIONICS 
.0 .0 
FURNISHINGS AND EQUIPMENT 
.0 .0 
AIR CONDITIONING 
.0 .0 
ANTI-ICING 
.0 .0 
SYSTEMS AND EQUIPMENT TOTAL 
,0} ( .01 
WEIGHT EMPTY 
CREW AND BAGGAGE-FLIGHT, 
.0 
, 0 
. 0 
.0 
.0 
.0 
-CABIN, 
.0 
UNUSABLE FUEL 
.0 
ENGINE OIL 
.0 
PASSENGER SERVICE 
. 0 
CARGO CONTAINERS 
.0 
OPERATING WEIGHT 
PASSENGERS, 
.0 .0 
PASSENGER BAGGAGE 
.0 .0 
CARGO 
.0 .0 
ZERO FUEL WEIGHT 
.0 .0 
MISSION FUEL 
. 0 
RAMP (GROSS) WEIGHT 
.0 .0 
& NONCRUISE SEGMENT RESULTS 
CLIMB PROFILE DATA FOR SEGMENT 1 
- - - CUMULATIVE - - -
WEIGHT ENERGY ALT MACH 
TIME DIST FUEL CL L/D 
.57 
.70 
.54 
3 .15 
.50 
.07 
! 6.85) 
41.52 
. 15 
.00 
.22 
,07 
, 00 
5.10 
47 .07 
.00 
.00 
27.60 
74 . 67 
25.33 
100.00 
2541. 
3155 . 
2445 . 
14129. 
2236, 
311. 
( 30778.) 
186535. 
675. 
0. 
983 , 
325 . 
0. 
22925. 
211444, 
0. 
0. 
124000. 
335444. 
113781. 
449225. 
VEL RCI PC TIME DIST 
THRUST /TMAX 
INCREMENTAL- -
FUEL 
446239. 1743. 0. .300 198.4 3400. 1 .00 .0 .0 133.3 
.00 .0 .0 .881 10.10 119703. 1.000 
445872. 3403. 0. .419 277.3 5208. 1 .39 1.5 366.7 260.2 
.39 1.5 366.7 .451 18.06 107400. 1.000 
445577. 5063. 0. .511 338.2 5590. 1 .31 1.6 295.6 387.2 
.69 3.1 662.3 .303 17.02 93916. 1.000 
445290. 6722. 1219. .535 352.6 5462. 1 .30 1.7 287.0 406.1 
Nov 1B% 
15:09:06 C L7-SHORT-FLOPS-OLJT 
. 99 
1.30 
•144716 
1.62 
444429 
1 . 94 
444140 
2 .23 
1.64 
1J154H 
3.03 
443245. 
3 . 42 
442936, 
3 . 35 
412618. 
4 .30 
44221-:: . 
4.20 
•141948 . 
:> . 3 3 
441593 
5.02 
441221 
6.59 
440B26. 
7.35 
440402. 
8.23 
439940. 
9 .26 
439425. 
10 .50 
438832. 
12 , 04 
439751. 
12 .26 
6 909 
638: . 
6 3-J3S 
10042. 
i 1522 
11701. 
5 1809 
13361. 
7 2099 
-. - 2t 
0 2391 
16630. 
5 2691 
18340. 
3 
2711 
4180 
5276 
5B0B 
I 
8161 
1 
9494 
. 2 
10609 
3 2994,1 
19999. 12104. 
2 3 3 0 3.3 
1 09 ]'=.'(). 
4 3 621.."; 
23319. 14609. 
30-0 3950.1 
24978. 1619B, 
34.0 -1 J 3 1 
2561!1. 17837. 
38.3 4 E S 6.0 
2021H. 19497, 
43.3 5018.5 
29957. 21156. 
4S.9 541J..6 
3I':17. 22816. 
55.5 5837.0 
33277. 24175. 
63.1 6298.9 
34936. 26135¬ 
71.3 (B14.fi 
36596. 27795. 
83.7 )4fl7.2 
36801. 2B000. 
85.4 748S.5 , 
" ' 
253 
296 
279 
286 
285 
2 83 
272 
273 
2 0 6 
274 
286 
301 
318 
336 
3 56 
376 
390 
423 
426 
16. 65 
546 
16.70 
55? 
16 .71 
487 
16.21 
596 
16.33 
612 
16 .21 
E3D 
16.07 
656 
15.65 
J67 
82 
15.31 
714 
US. S3 
^20 
15 .79 
724 
16 .06 
72 9 
16.28 
734 
16.47 
739 
16-63 
744 
16 .76 
749 
16 .76 
750 
16.76 
948513 
357.9 
93 662 
363.9 
88753 
381.0 
85726 
384.7 
B1161 
3*3.6 
77109 
402.9 
73695 
417.9 
71127 
422 .3 
67260 
427 . 2 
63433 
443 . 6 
61025 
445 . 4 
57457 
445,9 
• 663 
445.9 
50191 
445,9 
46531 
445. !) 
43944 
445.4 
40745 
445.9 
37 --5 
its . ° 
35401 
415.9 
3= 3 
1 .ooo 
5 . 
1.000 
5149. 
1.000 
S061. 
i .ooo 
4734. 
1 .000 
4466 . 
1.000 
..CO 
4086. 
I GOO 
3 7 78. 
1.000 
3465 . 
1.009 
Si 5 . 
I . 000 
29S0 , 
1 .000 
2649 . 
1 .000 
2324 
1 .000 
2033 . 
1.00D 
1753. 
1-000 
1467 . 
• 0 0 
121D. 
1.000 
949. 
1.000 
915 . 
1 . OOO 
.31 
.32 
.33 
.34 
.36 
.33 
.40 
.42 
. 46 
. 49 
. 53 
.59 
. 67 
, 76 
,o:, 
1 .03 
1 .24 
1.54 
. 22 
1.8 2BS.9 
1.9 286.8 
2.0 287.0 
2.1 289.4 
2.3 293.7 
2 . 5 
2 .7 
2 .9 
298 . I 
302 .9 
300 . 1 
3.2 317.9 
3.6 32 8.9 
3 . 9 341 . 1 
4.4 354.8 
5.0 372.5 
5.7 395.1 
6.5 42.3.4 
7 . 7 462 . 0 
9.2 
13-4 
1.6 
515 .1 
593 .2 
91.1 
DESCENT PROFILE DATA FOR SEGMENT 6 
- CUMULATIVE -
WE! OUT F?L E RGY 
- - INCREMENTAL- -
TIME DIST FUEL 
400. "» 
395.9 
• i. ;• 
406.7 
410.3 
412 . 4 
42 B . 3 
417 .3 
407 .2 
4 2 1. 7 
406.4 
385.9 
365.0 
345 .0 
325.9 
307.6 
290 . 0 
273 . 3 
271 .3 
+ TIKE DIST FUEL CU L/D THRUST /TMP.X 
228783 1743 . 0 300 l'"> 4 1147 . 0 00 0 0 133 3 
.00 0 . 0 17.53 0. .000 
228929 3403 , 1623 3 00 200 ^. 1165. 0 -i 44 4 8 -146 0 129 7 
4 -1 ,44 4 8 -140 . N 464 17 .42 o. ,UU0 
229066 SS603 . :<I i 204 • •! -1193. ^ -i 41 4 7 -136 9 129 2 
•1- -2 . 84 9 5 -0.82 .8 467 1 7.39 0 . . OOO 
229i94 S722 . 4763 322 209 3 1L121. 0 -i 38 4 1 -128 2 12 B 6 
-4-12 14 3 -411 . 0 469 17.36 0 • .000 
259314 6382 . 6355 331 214 •: - 125D. 0 -i 34 4 1 -119 8 128 2 
-5 .56 19 0 -530 . n 471 17.33 0. -000 
229420 15042. 1922 340 21B B - 12B1 . 0 -i 31 4 7 -111 5 127 7 
+ -6,87 2 i 7 -642 . 3 4 70 J 7 . 10 ). .000 
229529 11701. ^486 3 50 220 7 101.. . 0 -l 0 :-, 4 7 -103 5 127 2 
+ - 8.10 I8 4 -745 . 9 475 1/ .27 0 . .000 
. *024 13361. 11044 : -.0 228 8 - 1 344 . 0 -l 20 4 7 -95 8 126 6 
+ -9.40 33 1 -Bll . 6 477 17 .24 . ooo 
13 15020. li. •- 370 233 » - 137/ . 0 -i 22 4 7 -88 2 126 C 
10.62 •' ' a -929 .8 480 17 .20 .000 
229793 166B0. 14140 3B1 239 2 1 J 1 0. , 6 • 0 1 : 4 7 -SO 8 1/5 4 
* 11 . 61 42 1 -IOIL/ 482 17 .16 0. .000 
229667. 1B340. 15690. .392 
17.12 
401 
17,02 
406 
16.78 
116 
16.63 
405 
-6-40 
lit 
06.22 
44 1 
15.95 
450 
15.63 
230225. 30617. 280OO, .481 
+ 21.29 93.0 -1446.6 .543 16.31 
230267. 33277. 26000. .581 
+ 22.16 87.6 -1483.B .373 16.92 
23Q307. 34936. 28000. .6*6 
+ 22.A6 91.9 -0504.2 .283 15.07 
230044. 36596. 2B0C0. .Til 
+ 23.40 95.7 -1560.8 .229 12. -Jh 
23034R. 36801. 28000. ,750 
+23.46 96.1 1065.0 .223 12.70 
r 12.97 47.2 1084.2 .460 
229933. 19999. 17256. 
* 14.11 51.8 -1150.6 493 
229993. 21559. 18875. 
+ 15.22 56.4 -1209.8 .513 
230045. 23319. 20444. 
• 16.32- 61.0 -1202.2 .524 
23U03Z. 2497,1. 22013. 
•f;. 107,35 65.5 -1308.8 .536 
230133. 26638. 23591. 
+ 18.38 70.0 -1349.9 .5C1 
230169. 28298. 25175. 
+ 19 . 3R 74.3 -1J85.7 . 5R 
230195, 20 57. 26762. 
+ 0 0.35 78.•• -1416.6 .588 
244 
248 
250 
254 
258 
2 62 
265 
268 
285 . 
345 . 
398 
440 
445 
ITERATION RANGE = 2500.000 
6 
• 
9 
0 
8 
0 
8 
O 
8 
0 
U 
0 
0 
0 
0 
0 
o 
o 
FOR 
-1447, 0 -1.16 
:18- 0-1.13 
.000 
•1514 . 0 -1.11 
.ooo 
•1552. D -1.08 
.000 
0003. 0 -1,06 
.ooo 
1 •• J d 0 
.000 
•1686. 3 
. 000 
•1740. 0 
.000 
•1774. O 
770 
•2067. 0 
. ooc 
2661. 0 
.000 
3437. 0 
.000 
35 55, 0 
. 000 
GROSS WE 
. . „ 
l.DD 
-.97 
- .94 
-.86 
-.70 
- . 54 
- .06 
# SIZING AND PERFORMANCE RESULTS 
CONFIGURATION DATA AFTER RESIZING (IF ANY) 
•!.RA:0 ,MC VOOJTI: R bOU'TY I • ! •: 13 . 7 LB 
PAYLOAD 1I4O0O.0 LB 
HftXIUDIl FUElj 11373.1.1 LB 
GROSS WliOGHT 44 322 4.9 LB 
REFERENCE WING AREA 3800.00 SQ FT 
WING LOADING 110.0:0 L3/SJ 
THRUST PER ENGINE 40700.0 LB 
ENGINE SCALE FACTOR 1.0000 
THRUST-WEIGHT RATIO .3 624 
4.7 
4 .7 
4.6 
4 . € 
4.5 
i . 5 
4.4 
4.3 
4 . 4 
4 . 5 
4.3 
3.8 
.4 
-73.6 
-66 . i 
-59-2 
-52.4 
-46.6 
-•111 
-35.3 
-30.9 
-3 0.0 
-37 . 2 
-40 . 4 
-36.5 
-4 .2 
449224.6E 
124 .7 
122 .6 
.17.9 
115,5 
112 .9 
109.8 
106.5 
IB ( .0 
111 .5 
162 . 6 
013.8 
265 . 0 
271 .3 
hi NUMBER 
SEGMENT 
T END 
TAXI OUT 
TAKE OFF 
CLIKB 
+ O .3 50 
CKUISE 
IMTIAL fUEMLB) 
ALTITUDE (FT) I.OX EMISSI LB) 
WEIGHT!LB) SEGMT TOTAL SEGMT 
START ENP SEGHT TOTAL 
MISSION SUMMARY «-« 
TIME(MINI DISTANCE(N MI) 
TOTAL SEGMT TOTAL 
! 49220- . 
148105-
1120. 
13 6 5. 
446225. 7489. 
0. 2 6000 
433751. 7Q336. 
• 0 ,700 2R000. 2B0O0. 
RE'.SAKL 3684.S. O. 
0 .750 2R000. 28000, 
REFUEL 244415. 200O. 
0 ,750 S800O. 2SO0O. 
CRU1 T.1, 2424 15. 12 067. 
1120 . 
2986 . 
1.0474 . 
.00 
30810. 
. 00 
80J1O. 
.00 
82B10. 
.00 
91877. 
.00 
. 09 
. • 0 
, 00 
15,0 
2 .0 
207 . 6 
.0 
0 :"• 
54.3 
15 . C 
17 . 0 
29.3 
286 . 9 
286.9 
391.9 
446.3 
1914.6 
.0 
.0 
4 03 .9 
35,4 
2000.0 
2000.0 
20DD.0 
2403.9 
MAC 
OT/'.r. 
.30 
.75 
.75 
. 75 
.75 
Nov 18 96 
15:09:06 C17-SHORT-FLOPS-OUT 
0 .750 28000. 28000. .00 .00 
DESCENT 230318. 15*5. 96442. 23.5 
.JOO 28000. 0. .00 .00 
169.7 BS.l 2500 0 
.01751 
444140. 
13361. 
27199. 
16.329 
384.75 
.00771 
408.7 
13 .28 
.0 
1 
12 .7 
.000 
50S5. 1. OOOOO .61473 4519.1 
; ... EI •. 
TAXI IN 
Z-EKO FUEL 
I/F J 1735 9. 
149 . 2.0 
DESIGN RANGE 
FLIOHT TIME 
2500 . 0 
152 .7 
BLOCK TIME = 7,86 HOURS 
BLOCK FUEL = 96591.3 POUNDS 
TOTAL NtTFtOCEH OXIDES EMISSION'S = 
ATA TRAFFIC ALLOWANCE = 
AIR MANEUVER - 44.6 
KlRFORi- THAI-KIT ALLOWANCE - L7 . 4 
A I? WAY D7 5TAMCL FACTOR = 1 IL . 0 
ATA RANC-3 - 2300 . 0 NAUTICAL MILES 
1 
H DETAILED FLIGHT SEKWENT SUMMARY 
0. POUNDS 
13 2.0 NAUTICAL MILES 
446239. 
.SS031 
445230. 
.26856 
. 01733 
415003. 
444716 
.01769 
473329 . 
.77335 
.01719 
444140. 
31. •. 
RTTUDE MACH NO. DELTA T 
LIFT L/i 
ENERGY VELOCITY 
DRAG SP RANGE 
O. 
443239. 
1743 . 
.337114 44 196 
445872. 0. 
.45037 445972. 
3403 . 
.02*97 24695. 
102P6 445577. 
5063 . 
111780 26186. 
3000 
10.097 
198.44 
IS.055 
277.25 
.00433 
.5112 
17.016 
• 3.17 
.00563 
445290. 
3722 . 
26741. 
2711 . 
.29257 415033. 
8732. 
,01752 26652. 
4185 . 
59 444716. 
10012 . 
5276 . 
414129. 
274 23 . 
6808 
J.u.632 
352.59 
.DO622 
.5462 
16.697 
3 57.69 
.00S52 
.5582 
16.711 
363.86 
-3U-,32 
.5367 
16.206 
380.96 
.00724 
. 5557 
Q 
TIME 
NOX 
. 03 
133 .3 
17 .00 
.0 
.39 
260 .2 
17.39 
. 0 
387 .2 
17.69 
.0 
406 . I 
17.99 
.0 
400.3 
18 .30 
. 0 
.32 
395. 9 
18 . 62 
. 0 
. 33 
419 . 9 
18 . 94 
.0 
DELTA D P 
PCODE 
DIST 
P.NG YHH 
,0 
.033 
.34 
] . 5 
. 035 
1 . 6 
3.1 
.000 
4 . 3 
. ooo 
1.8 
6.6 
.000 
1 . 9 
1 
8.5 
. 000 
2 .0 
1 
10-5 
. ( 0 
2 .1 
1LTA F THRUST FUEL FLOW EX POW 
FUEL T/TMAX 
0 . 
2986 . 
3 3 . 
3352. 
296 . 
1643 . 
2 87 . 
3935 . 
287 . 
42 72 . 
287 . 
4509 . 
287 . 
4796 . 
289 . 
SFC DH / DT 
119703. 56725. 3430.4 
1.00000 ,47388 
107400. 57392. 5208.0 
1.00000 .5343S 
98916, 58017. 5589.£ 
1 . 03300 , 0 
94858. 56645. 5462.1 
1.OD000 .59716 4057.5 
91662. 54913. 5294.3 
1.03OO0 .59908 1H3B.0 
8:7753. 53354. , I J :•: 
55115 4 6.71.7 
j2589. 5061.1 
1.0-73OO . C1345 3370.6 
443846. 
.2843 5 
.01756 
443548. 
.2830 7 
443245. 
.27231 
4423 3 3. 
.2/333 
44261 '-. 
.23603 
412289. 
.77409 
31 7 I 
441946. 
.28616 
.77333 
44 n. 
.1DH6 
.01907 
4J1227 
.31811 
.01.331 
440826. 
.33624 
.02066 
4101D2. 
.35565 
. 02160 
439940. 
.37644 
439135. 
.33870 
31161. 4ST332 
8161. 
4433i46 . 
15020 . 
27381. 
9434 . 
443548. 
16660. 
276D1. 
10609, 
443245. 
1B340. 
I 
.'IN.. 
4 1^: A. 
19999. 
28132 . 
13580, 
41251B. 
21659. 
27985. 
116 •} . 
442289. 
23319. 
23S8ti. 
16196. 
441948. 
24973. 
2 84 5 6 . 
17837. 
441593. 
5661H. 
27950. 
19197. 
441221. 
26298. 
27479. 
21156. 
440826. 
29957. 
2-7691 , 
22316. 
140402. 
31617. 
25715. 
21175. 
1 •••••IN. 
33277. 
26154. 
26135. 
419425. 
3 4 356. 
.(125 
15.2¬ 
333.62 
.00 -1 
.5300 
16.07U 
402.90 
.00B75 
.33 31 
15.648 
417,27 
.009^0 
.6668 
15 .745 
422 . 32 
. C0987 
. 6782 
15.316 
427, 18 
.01056 
.7070 
15.31S 
443.56 
.01121 
.7 142 
15 . 51; I 
443,7 7 
. 01196 
.7196 
15.794 
445.68 
.01283 
.3243 
16.056 
445.88 
. 01384 
.7291 
16.27d 
415.33 
.01485 
.7341". 
16.467 
445.88 
.01595 
.-nso 
16 .631 
415.83 
.01726 
744J 
16-758 
445.88 
. 3 6 
410.3 
19 . 34 
. 0 
.38 
. 4 
20.42 
.0 
. 42 
417 . 3 
2 :• . LI 5 
.46 
407 .2 
21 .30 
. 0 
.49 
424.7 
21 .80 
.0 
.53 
406 . 4 
2 2,33 
.0 
.59 
385 .9 
22 .92 
.0 
.67 
3G5.0 
23.59 
. 0 
.73 
.0 
325 . 9 
25 .23 
.0 
1 
307 
03 
6 
26 .26 
. 0 
1 
290 
3 • 
3 
2 . 3 
1 
15 .0 
. 000 
2.5 
17.5 
.00(1 
2 .7 
1 
2".3 
,O00 
2 . 9 
1 
23 .2 
.000 
3.2 
1 
26.4 
.3 30 
3 . 6 
1 
30.0 
. 003 
3.9 
1 
34 . 0 
.033 
4 .4 
1 
•3.3 
,003 
5 . 5 
1 
43 .3 
.000 
5.7 
48, 9 
.300 
. 055 
63 . 1 
.3' 
9.2 
294. 77150. 47796. 4466.0 
5379. 1.00000 .61363 3752.4 
298. 71695. 46034. 4240.1 
5677. 1.00000 ,61 466 7-7 71.3 
7.73. 71127. 357,11. 4086,4 
5930. 1.00000 .63733 2733.9 
309. 67260. 42791. 3 3 3.0 
62B9. 1,00000 .63620 3540.6 
118. 
355. 
63433. 40447. 14 64 . 6 
.1337 . 1 .00000 . 63 '63 3222 . 0 
329. 31375. 33377 3261.6 
6936. 1.00000 .64820 2084.5 
341. 57457. 37187. 2959.5 
7277. 1.00000 .64721 2980.0 
163 - 34751. 2648.6 
27 .50 
7632. 1.00300 .64517 2731.3 
373. 50191. 322.74. 2324.3 
8004. 1.00000 . 6i.;0j 2486.5 
395. 46931. 30017. 2033.2 
S399. 1.00000 .63931 2J73.8 
423. 43341. 27339. 1753.1 
8823- 1.00003 .6^734 1893.2 
462. 40713. 25313. 1466,9 
9285. 1.00000 .531U 3 3 13,3 
5 1 - 17596 
9800. 1.35000 .63180 1338.1 
Nov 18 96 
15:09:06 C17-SHORT-FLOPS-OUT 
.01379 16222. 
43B932. 
. 02255 .0?' . 
438751. 
.42562 
.02540 
SEGMENT 
V. • 0|T 
0 IT 
CD RAG 434751. .42562 
.02540 
432000. 
.41904 
.02505 
416000. 
.40355 
400000. 
.38800 
.023 54 
384D00. 
.372 50 
.022!!7 
36B415. 
.3! 39 
.02224 
S"EETJT WEIGHi 
01.IF 
244415. 
,.- , ,10 
,01799 
3EGM.ENT WSJ • IH1 
CLIFT 
27795. 
438*32. 
36596. 
26179. 
26000. 
30,80 : . 
261B6. 
.D1B57 
.7493 
16.763 445.sa 
.02 31 
.7500 
16 .755 
445.88 
. 02020 
2 CRVTSE 
ALTITUDE MACH NO, 
IilF L/D 
ENERGY VELOCITY 
DFAG SF RANGE 
2B000. .7500 
.31 1. 16.755 
35801. 445.00 
261H6. ,O20>4L 
28OQ0. 
432OC0. 
3*801. 
25320. 
28000. 
416000. 
36HQJ-
24998. 2S000. 
400000. 
3 & a i • i. 
24270. 
2B00O. 
384000. 
0 00 L . 
23581. 
2E000. 
368415. 30801. 02001 
.7500 
16.731 
445.80 
.02609 
.7500 
16.641 
445.83 
.02676 
.7500 
16.481 
445. o 
.0273B 
. 7500 
16.2B5 
445.6E 
.02799 
.7500 
16-066 
4 45.y8 
.D2B58 
. 0 
1 . 54 
273 .3 
29 .04 
.0 
.22 
271 . 3 
29.26 
DELTA T 
Q 
TINE NOX 
.00 
271 . ] 
29.06 
. 0 
23 . 54 
271 . 3 
52 . 80 
. 0 
56.90 
271.3 
109.70 
.0 
58 .28 
271.3 
167.98 
. 0 
59 . 60 
271 . 1 
227 . 5B 
.0 
59 .32 
271 .3 
0 86.90 
.0 
3 REEF. 
AJ.l'lTUDE I.J 
ENERGY 
DRAG 
MACH NO. DELTA T 
L/D 0 
VELOCITY OlilL 
SP RANGE NOX 
28DDO. .7500 .00 
241415. 13.171' 271.3 
16801. 445.68 286.90 
16 3. .03319 .0 
4 REFUEL 
ALTITUDE MACH NO. DELTA T 
LIFT L/D 
ENERGY VELOCITY TIME 
DRAG SI- KANOIr: NOX 
. 000 
11.4 
1 
83 .7 
. 000 
1. 6 
1 
65.4 
. 
DELTA D 
PCODE EIST 
ENG PAR 
.0 
2 
35 . 4 
. 000 
175.0 
2 
260.3 
.000 
422 . 8 
2 
683 . 2 
. 000 
433 . 1 
2 
1116 , 3 
.000 
442.9 
2 
1_ 9.0 
. OOO-
440 . 8 
2 
2000.D 
. OOO 
DELTA D PCODE DIST 
ENG PAS 
.0 
2 
2000,0 
.000 
DELTA C IT
 r-K 
DIST 
UNG PAH. 
393 . 
10393. 
81 . 
10474. 
Ftifst 
10474. 
17225. 
35401. 22286. 
1.00000 ,62933 
948 . 9 
1079.4 
49225. 
1 • JU . 
35080. 22073. 915.3 
1.00000 .62921 932,1 
i'RRTJ.ST FUEL PLOW EX TOW 
T/TMAX SFC DH/DT* 
2 618 6. 17216. 
.85065 
25820. 
846611 
2499B. 
. B1971 
. 65977 
17087. 
.66176 
16661. 
.66649 
24270. 16284, 
.79585 .67094 
.77324 
15932. 
.67562 
BD810. 
FUEL 
443 . 6 .C 
4 88 .7 
.0 
596.8 
.0 0 00
 , 3 
, 0 
813 .2 
.0 
22931. 15602. 927.1 
.75194 .68037 .0 
THRUST FUEL FLOW EX ?CW 
T/TMAX (BfC DH/DT* 
18545. 13433. 2207.7 
.60813 .72<m .0 
THRUST FUEL FLOW EX POW 
T.'TMAX SFC DH/DT' 
242415. 
.23516 
.01793 
SEGMENT 
WEIGHT 
CLIFT 
242415. 
.23516 
.01793 
2 40000. 
.23281 
.01786 
230346. 
. 22345 
.01759 
SEGMENT 
WEIGHT 
Cl.l KT 
230348. .2.A45 
230344. 
.22878 
230397. 
, 28348 
230267. 
.37253 
.02203 
230229. 
.54345 
230199. 
.53840 
. 1763 Z30169. 
.56893 
2B000. .7500 
242415. 13.114 
36801. 445.86 
18465. .03327 
5 CRUISE 
ALTITUDE MACH NO. 
LIFT L/D 
ENERGY VELOCITY 
DRAG SP (LANGS 
23000. 
242415. 
3S801. 
18485. 
2BO00. 
240000. 
36B01. 
13112. 
2B000. 
230308. 
3 6601. 
161J5. 
. • i0 
13 .114 
415 . 8S 
.03327 
.7500 
13.O30> 
443 . 8(3 
.03335 
.7500 
12.702 
445.66 
.03369 
6 DESCENT 
ALTITUDE MACH NO. 
LIFT L/D 
ENERGY VELOCITY 
DRAG SP RANGE 
28000. 
23C348. 
366D1. 
18135. 
280 : 3. 
230344. 
36596. 
17740. 
280OO. 
230307. 
34936. 
15267. 
2EO00. 
23D2 67. 
3 3277. 
13613. 
23000. 
23022;-. 
3 i 60 7 . 
14114. 
26762. 
23Q199. 
29957. 
147^4. 
25175. 
• 1 . 
.7500 
12.702 
445.63 
.10258 
.7412 
12.985 
440.65 
.10286 
. 6658 
10.065 
395.83 
. 10505 
,5801 
16.013 
315.21 
.1097B 
.1606 
16.313 
285.63 
,14156 
.4495 
15.635 
269.64 
.10982 
. 4115 15.947 
ill... 
271 .3 
3 91.90 
. 0 
TIME 
NOX 
. 00 
271.3 
191.90 
. 0 
10.79 
271.3 
402,69 
.0 
43.56 
271. 3 
446.25 
. 0 
DELTA T 
Q 
TIME 
NOX 
.00 
271.3 
446.25 
. 0 
. 06 
265 . 0 
446.31 
.0 
446,85 
. 0 
. 70 
161. 6 
447.56 
.0 
. 86 111.5 
44B.42 
. 0 
. 94 
103.0 
449.36 
.0 
2000.0 
.000 
OEI.TA D : . . i
 E 
DIET HNv'j FAR 
.0 
2 
0.0 0 0.0 . o-oo 
80.2 
2 
2080.2 
.000 
323 .7 
2 
3403.9 
000 
DELTA D 
PCODE DIST eee . ar 
. o 
o 
2403.9 
.000 
0 
2404.3 
. 000 
3 .3 
O 
2403.1 
.000 
4 .3 
0 2*12
 - 4 
.000 
4.5 
0 
2 41 7 . 
003 
4 . 4 0 
2421 . 4 
. 000 
SOW. 1U434. 13404. 2237.3 
82810. .5061? .72512 .0 
DELTA F THRUST FUEL FLOW EX POW 
FUEL T/TMAX SFC ISi/UT* 
0. 18485. 13404. 2237,3 
30.SIO, .CM: 3 .72512 .0 
2415. 12. 133 68. 2273.4 
85225. .60376 .ii606 .0 
"052. 18135. 13233. 2423.1 
94877. .55465 .72072 .0 
DELTA F THRUST FEET FLOW EX POW 
FUEL T/TMAX SFC DH/DT* 
0. O. 4346. -0O04.8 
.00000 .00000 .0 9 0 04 0 . 
4 . 
94631. 
0. 4284. -3436.6 
.00000 .00000 .0 
37. 0. 3768. -2600,8 
94918. .00000 .00000 .0 
40. 
94958. 
37. 
94995. 
30. 
0.4.02 5 . 
31 . 
0. 3145. -2C66.9 
.00000 .00000 .0 
0. 2019. -1774.5 
.00O0O .OHOOO .0 
0. 1793 . - ! 14 .' .1 
.00000 .00000 -1310.4 
0. 2030. -1696,4 
Nov TK% 13:09:06 
.TOO^ 23D133. 
.55110 
230092 . 
.53646 
.03261 
230045. 
.52432 
229852. 
. s IN I 
279933 . 
.' !42 
229667. 
.4P512 
229793 , 
0 -•' 0 7.29713. 
.47963 
229601. 
.47721 
28298. 
1*433. 
235 -1 
230133. 
26638. 
14167. 
22013. 
230092. 
24973. 
1 • !. 
20444. 
23i •: , 
20 J 
13837 • 
18875. 
229993. 
21659. 
13709. 
17256. 
229933. 
19999. 
13510. 
15690. 
229667. 
16340. 
13429. 
14146. 
229793. 
16480. 
13391 
12«98. 
229713. 
15020. 
..• .6. 
1 . '.'44 . 
229624. 
13361. 
13333. 
265.5^ 
.15080 
. 4313 
16.222 
262 .16 
11528 
.4247 
16.449 
258.80 
. 1D251 
.41 --.=. 
16.625 
2 04 . J3 
.03 130: 
.4063 
16.777 
.0-0 55 
. 4 009 
17.019 
24 S . 01 
.07393 
.3915 
17.117 
244.64 
,06673 
. 3806 
17.160 
239.23 
.06"073 
.3700 
17.199 
233.94 
.05S6I 
.3598 
17.235 
228.77 
.05: .9 
450.33 
. 0 
1.00 
109 . 8 
40 1 .33 
.0 
1.D3 
112.9 
452.36 
. 0 
1 
115 
453 
1 
117 
06 
5 
41 
0 
OS 
9 
454.50 
. 0 
1 
122 
11 
6 
61 
0 
1.13 Lli .
 7 
456.74 
.0 
1 . IS 
125.4 
457.90 
.0 
1 . 19 
126.0 
459.09 
.0 
1 
126 . 
22 
6 '-. 1 
0 
242*.7 
.000 
4.4 
0 
2430.0 
.000 
4.5 
0 
2404.0 . 000 
a 
2119.0 
.000 
2443.6 
. 000 
2448.2 
.000 
4.7 
0 
2452.6 
.000 
4.7 
0 
2407.5 
.000 
4.7 
0 
2462.2 
.0 00 
4 .7 
0 
2466.9 
.' 10 
95056. 
36. 
95092. 
41 , 
95133. 
47 . 
95180, 
52, 
95232 . 
59. 
95291. 
56 . 
9535R. 
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95431. 
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95512. 
88. 
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.ooooo 
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.00000 
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C17-SHORT-FLGPS-OUT 
.00000 -1638,1 
2276. -:6'-.7.9 
,00000 -1586.9 
2525. -1000.4 
.00000 -1535.7 
2775. -0552.2 
.00000 -1487.1 
3038. -1513.6 
. OOOOO 
3666. 
,00000 
14 8.7 
3367. -14<.0 ,3 
,00000 -1461.3 
!47 .3 
,8'. .3 
3939. -1411.8 
,00000 -1329.9 
0. 4206. -1377,5 
.00000 .00000 -1000.0 
-1344.2 
229066. 3205. 
.45651 229066. 
5063 . 
.02633 1317]. 
223929. 1623. 
.40433 228! 20. 
3103 . 
.02665 13110. 2261 S3 .
 0. 
.45159 228783. 
3 743 . 
.02577 1305 1. 
. 3131 
17.391 
204 .84 
.01535 
.3048 
17.422 
200.50 
03367 
.3000 
17.526 
193.44 
.0317 7 
1. 3 E 
129.2 
466.87 
.0 
1-41 
129.7 
•166 28 
1.44 
133 . 3 
469.71 
. 0 
,: . •/ 
0 
2490.5 
, 000 
4 . 7 
0 ?: • o 
. ODD 
4.8 
0 
2500.0 
. DOO 
137 . 
96296. 
14 6 . 
96442 . 
0 . 
.00000 
0 . 
. OOOOO 
0. 
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57 14. 
. ooooo 
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. ooooo 
6246. 
. ooooo 
-1192 . 8 
-1147.6 
-1165.4 
-1123 , 7 
-1016,6 
-1130 . 8 
* DH/DT IS THE AVERAGE OVER THE STEP. 
+ ND OF THE STEP. 
HOOJ/VAR/CONSTR SUMMARY 
EIIE1. y.l:i\\\£ VAF? - ROFF FARLDG 
H SV1 TP. SWEEP TCA VCMN OH 
H3761.1 2500.0 126.4 4861 
+ 300.0 .000 25.00 .0210 .750 45000 DESIGN TIT OPR FPR BPR + AI..T T.HAU.OT SEC
 CVEFF CDT CDP 
28.00.0 30. BOO 1.5000 2.9000 1.000 
+ 45000. 3332. .6129 .2963 1209.0 80.47 
VAPP- 12 6.4 
J?ftJlOFE- 4 B ( 1 . 
FARLDG" 5862. 
THE OTHER DATA ARE JNEITANTANEOUS AT THE E 
5862. 51476 IIS.2 
TR 
AMFOP. SSFOR 
W/S T/W 
29730. 
.3 62 
(SLS) 
GW AR THRUST 
449224.9 7.200 40700.0 3 
ST VJFT (CHUIEK) BACH 
30.8 1673.8 .75 
.00000 .00000 1273.E 
09529. 
.0 
.02751 
94 86. 
229529. 
11701. 
0 3292. 
.3496 
17.269 
223,71 
.04734 
V 
46: 
.25 
.2 
. 56 
.0 
4 . 7 
0 
2471.6 
.000 
96 . 
95596. 
4726. -1311.9 
.00000 .00000 -1246.9 
229425. 
.47238 
'29314 . 
•1 7085 
229194. 
.4 £990 
,03701 
792 3 . 
020 122. 
10042. 
13262 . 
63 55. 
229314. 
8382 . 
13 2 32 . 
4783 . 
229194. 
6722 . 
13 >. 
.3401 
17.300 
218.77 
.04394 
.3308 
17.330 
213.97 
. 4( '3 
.3217 
17,359 203.29 
.03825 
1.28 12
 7.7 
462.84 
.0 
1 .31 
126.2 
164.15 
. 0 
I .34 
128.6 
165.49 
.0 
4 .7 
0 
2476.3 
.ooo 
1.7 
0 
240!! . 
.000 
4.7 g 
24 . . . OOO 
104 . 
95800. 
112 . 
95911. 
120 . 
96031. 
-1280.6 
.00000 .OOOOO -1220.7 
0. 
. OOOOO .00000 -1195.3 
5472. -1220.9 
.00000 .00000 -1170.3 
C17-MIDDLE-FLOPS -IN 
C1T Short Mission 
SOFTION 
MPRINT=1, 
I0PT=1, 
IANAL=3, 
NOPRO=0, 
NOISE=0, 
ICOST=0, 
IFITE= 0, 
INENG=1, 
ITAKCF=0, 
ILAND=0, 
SEND 
SWTIN 
MYWTS=0, 
ULF=2.25, 
SPAN=167.4, 
FCOMP^O.15, 
NETAW=2, 
£TAW=0.0, 1.0, 
CHD=32,82, 13.13, 
TOC=0.135, 0.107, 
ETAE=0.301, 0.591. 
SHT=845.0. 
SWPHT=27.0, 
ARHT=5.0, 
TCHT=0.035, 
HHT=1., 
SVT=685.0. 
SWPVT=41.0, 
ARVT=1.0, 
TCVT=0.11, 
NFIN=2, 
SFIN=72.55, 
-ARFIN=l.-09, 
TRFIN=0.325. 
SWPFIN=50.0, 
TCFIN=0.10, 
XL=159,1, 
WF=21.06, 
DF=23.00, 
NEW=4, 
NEF=0. 
WENG=7100. , 
XNAC=12.23, 
DNAC=6.23, 
FULWMX=182720.0, 
FULFMX=0.0, 
NFLCR=3, 
CARGF=1., 
CARGOF=l12000.0, 
SEND 
SCONFIN 
DESRNG=3 900., 
HTVC=1.0, 
VTVC=0.10, 
GW=650000. , 
THRUST=40700. , 
AR=7.2, 
SW=3800.0, 
SWEEP=25.0, 
TCA=.121, 
VCMN=0.75, 
CH=45000.0, 
SEND 
5AERXN 
MYAERO=0, 
AITEK=1.2, 
VAPPR=115.0, 
FLTO=4400., 
FLLDG=3200., 
CLTOM=3.585, 
SEND 
SENGDIN 
IGENEN=1, 
IDLE=1, 
NONEG-1, 
IXTRAP=0, 
DFFAC=0. , 
EMACH-0.80, 
SEND 
0.75, 0.70, 0.60, 0.50, 0.40, 0.30, 0,20, 0.10, 0.0, 
$ENGINE 
IENG=2, 
IFILE='TFNSEP ' , 
TFILE='ENGTAB' , 
OFILE='ENGOUT' , 
OPRDES"30.S, 
BPRDES=5.9, 
TETDES=2800., 
YEAR=1995., 
IGVW=-1, 
SEND 
SMISSIN 
FACT=1.0, 
ISKAL=1, 
MSUMPT=1, 
IATA=0, 
IFLAG=2, 
IRW=1, 
ITTFF=1, 
TAXOTM=15.0, 
TAKOTM=2.0, 
TAXITM=2.0, 
NCLIMB=1, 
CLMMIN=0.3, 
FWF=-1., 
IFAACL=0, 
IFAADE=0, 
NCRUSE=1, 
IOC=2, 
CRHMIN=0.3 , 
CRMACH=0.75, 
CRALT=280O0., 
IVS=1, 
IRS=1, 
TIMMAP=2.0, 
ALTRAN=500.0, 
SEND 
START 
CLIMB 
CRUISE 
RELEASE 
REFUEL 
CRUISE 
DESCENT 
END 
3400. 
112000. 
-2000. 
500. 
105 . 
15:09:05 
i 
8TITLE, BEGIN INPUT DATA ECHO 
CIT Short Mission 
8 NAMELIST SOPTION 
PROGRAM CONTROL, EXECUTION, ANALYSIS AND PLOT OPTION DATA 
DESCRIPTION NAME VALUE DIMENSIONS 
TYPE OF PROBLEM IOPT 
ANALYSIS OPTION IANAL 
MAIN ENGINE DECK SWITCH INENG 
DETAILED TAKEOFF SWITCH ITAKOF 
DETAILED LANDING SWITCH I LAND 
COST CALCULATION SWITCH ICOST 
TRANSPORT/FIGHTER SWITCH IFITE 
TAKEOFF PROFILE FOR NOISE NOPRO 
PROFILE OUTPUT FILE SWITCH NPFILE 
NOISE CALCULATIONS SWITCH NOISE 
MASTER PRINT CONTROL MPRINT 
XFLOPS DATA PLOT SWITCH IXFL 
AERO POLAR PLOT SWITCH IPOLP 
THRUST DATA PLOT SWITCH IPLTTH 
HISTORY DATA PLOT SWITCH IPLTHS 
EXCESS POWER PLOT SWITCH IPLTPS 
ft NAMELIST SWTIN 
GEOMETRIC, WEIGHT, BALANCE AND INERTIA DATA 
DESCRIPTION NAME VALUE DIMENSIONS 
MAX OPER MACH NUMBER VMMO . OOOO 
ULTIMATE LOAD FACTOR ULF 2.2500 
REF WEIGHT NUMBER NWREF 3 9 
CG REFERENCE LENGTH CGREFL 1909.2 
X FOR START OF CGREFL CGREPX .0 
SWITCH TO COMPUTE WEIGHTS MYWTS 0 
DESIGN GROSS WT. (RATIO) DGW 1.000 
HYDRAULIC SYSTEM PRESSURE HYDPR 3000. 
IN 
IN 
WING DATA 
DIHEDRAL(POSITIVE) 
GLOVE AND BAT AREA 
SPAN 
DIH 
GLOV 
SPAN 
CONTROL SURFACE AREA RATIO FLAPR 
FRACTION OF COMPOSITES FCOMP 
AEROELASTIC TAILORING FACT FAERT 
STRUT BRACING FACTOR 
VARIABLE SWEEP FACTOR 
FSTRT 
VARSWP 
.000 
-92.05 
167.40 
.3330 
.1500 
. 0000 
,0000 
.0000 
DEG 
SQ FT 
FT 
DETAILED WING DEFINITION DATA FOR 2 STATIONS 
STATION DATA 1 2 
0 Y/SEMISPAN ETAW 0000 1.0000 
0 CHORD/SEMISPAN CHD 32 8200 13.1300 
0 THICKNESS/CHORD TOC 1350 ,1070 
c LOAD PATH SWEEP SWL .00 .00 
c REFERENCE ASPECT RATIO ARREF 7 . 20 
REFERENCE THICKNESS/CHORD TCREF . 12100 
FRACTION OF LOAD ON DEFINED 
WING (OR REF WING AREA] PCTL 1.0000 
NO. OF INTEGRATION STEPS NSTD 50 
MIDDLE-FLOPS-OUT 
ENGINE LOCATIONS 
LOAD DISTRIBUTION CONTROL 
ETAE 
PDIST 
.3010 
2 .00 
. 5910 
HORIZONTAL TAIL DATA 
AREA 
1/4 CHORD SWEEP ANGLE 
ASPECT RATIO 
TAPER RATIO 
T/C 
LOCATION ON VERTICAL ' 
SHT 845 .00 SQ FT 
SWPHT 27.00 DEG 
ARHT 5.00 
TRHT .0000 
TCHT .0850 
HHT 1.0000 
VERTICAL TAIL DATA 
NUMBER OF VERTICAL TAILS NVERT 1 
AREA SVT 685.00 
1/4 CHORD SWEEP ANGLE SWPVT 41.00 
ASPECT RATIO ARVT l.OOOQ 
TAPER RATIO TRVT .0000 
T/C TCVT .1100 
SQ FT 
DEG 
WING FIN DATA 
AREA SFIN 72.55 
ASPECT RATIO ARFIN 1.0900 
TAPER RATIO TRFIN .3250 
T/C TCFIN .1000 
1/4 CHORD SWEEP ANGLE SWPFIN 50.00 
NUMBER OF FINS NFIN 2 
SO FT 
FUSELAGE DATA 
NUMBER OF FUSELAGES 
TOTAL LENGTH 
MAXIMUM WIDTH 
MAXIMUM DEPTH 
CARGO AIRCRAFT FACTOR 
PASSENGER COMPART LENGTH 
NFUSE 1 
XL 159.10 FT 
WF 21.06 FT 
OF 23.00 FT 
CARGF 1.0000 
XLP 120.01 FT (CALC) 
LANDING GEAR DATA 
LENGTH OF MAIN GEAR 
LENGTH OF NOSE GEAR 
DESIGN LANDING WEIGHT 
SET WLDG TO END OF DESCENT 
CARRIER BASED AIRCRAFT 
XMLG .00 IN 
XNLG .00 IN 
WLDG 459875.0 LBF 
MLDWT 0 
CARBAS .00 
PROPULSION SYSTEM DATA 
NUMBER OF ENGINES ON WING NEW 4 
NUMBER OF ENGINES ON FUSE NEF 0 
BASELINE ENGINE THRUST THRSO .0 LBF 
BASELINE ENGINE WEIGHT WENG 7100.0 LBF 
WEIGHT SCALING PARAMETER EEXP 1.15000 
BASELINE INLET WEIGHT WINL .0 LBF 
INLET WT SCALING EXPONENT EINL 1.00000 
BASELINE NOZZLE WEIGHT WNOZ .0 LBF 
NOZZLE WT SCALING EXPONENT ENOZ 1.00000 
BASELINE NACELLE LENGTH XNAC 12 .23 FT 
BASELINE NACELLE DIAMETER DNAC 6 .23 FT 
FUEL CAPACITY OF WING FULWMX 182720.0 LBM 
(FUEL CAPACITY FACTOR FWMAX 17.506) 
FUEL CAPACITY OF FUSELAGE FULFMX .0 LBM 
ADJUST FUSE FUEL CAPACITY IFUFU 0 
AUXIL TANK FUEL CAPACITY FULAUX .0 LBM 
NUMBER OF FUEL TANKS NTANK 7 
ADDED MISC PROP SYSTEM WT WPMISC .000 LBF 
CREW AND PAYLOAD DATA 
FIRST CLASS PASSENGERS NPF 0 
TOURIST PASSENGERS NPT
STEWARDESSES NSTU -1 
GALLEY CREW NGALC
Nov 18 96 
15:09:05 C17-MIDDLE-FLOPS-OUT 
FLJUHT CREW NFLCfi 
WEIGHT P£H PXSsKNOES WPPASS 
BAGGAGE PER ?AS.<? EMOPJ! SPP 
CARGO IK WING CARGOW 
CARGO JN FVSELAGE CARflOF 
OVERR: • • MRA'-iCTERS FOR 1 • 
i 
165.0 
44 .0 
.0 
12000.0 
LBF 
LBF 
LBF 
LBF 
AUXILIARY :;EAR CGAI 
AUXILIARY TANKS CGAOT 
AMF.L AND NONFTA. :) GUNS CGAIMO 
MISCELLANEOUS USEFUL LOAD CGKIS 
. 0 ID 
.0 IN 
.0 IN 
. 0 IN 
WINU - TOTAL FRWI 1 OOOO 
WING WEIGHT FlftST TERM FRWI1 1 OOOO 
WING WEIGJ4T SECOND TFPM FRWI 2 : oc 
KING WEIGHT THIRD TERM FRU13 1 oooo 
HORIZONTAL TAIL FRKT i oooo 
VERTICAL TAIL FRVT : .0ODD 
WJUS VfiSTJCAL FIN FHFIN . oooo 
CANARD FRCAN l oo no 
FUSELAGE FRFU l oooo 
NOSE LANDING GEAR IRI ;;• l cuno 
MAIN LANT>;NG GEAR FT :. ••: l oooo 
NACELLES - TOTAL OR FfcNA 1 C 000 
AIR INDUCTION SYSTEM 
IHRUSI' Ri-iVEBssts - TOTAL WTHR oooo 
MISC RKOP(JL£10N SYSTEMS w i oooo 
FUEL SYSTEM wysvs 1 oooo 4 
-SURFACE CONTROLS FRSC E oooo 
AUXILIARY POWKR IRNIT WAPU : 00 DO 
INSTRUMENT GROUP WIN i OOOO 
HYUKAUI.1''S GROUP W! 1 YD l oooo 
:TRICAL QRlVV WELEC i oooo 
AVIONICS GROUP WAVONC l oooo 4 
ARl-IRTMENT C1R0UP WARM oooo 
FURNISHINGS GROUP WFURN l oooo 
AJH CONDITIONING GROUP WAC I oooo 4 
ANTI-ICING GROUP OH WAI i oooo 
AUXILIARY GEAR 
UNUSABLE FUEL WUF l oooo 
ENGINE GIL HQ IL l oooo 
PASSENSEK SERVICE OE AMMO W3XV l OOOO 
AND NCNFIXED WEAPONS 4 
CARGO ANE BAGGAGE C OH TAIN . WCON i OOOO 
OR MIS'•--::.].. USEFUL LOAD + 
AUXILIARY FUEL TANKS WAUXT I oooo 
FLIGHT CREW AND BAGGAGE . WFLCRB ; oooo + 
CABIN CKRW AX|/ BAGGAGE W5TUAB ! oooo 
ORl'ZQNTAI, CENTER OF GRAVITY DATA 
WING CGW - D 1 ii + 
HORIZONTAL TAIL C0HT .0 UM 
VERTICAL Tft^L j •/ i .0 . a 4 
WING VERTICAL FINS CUFIN .0 IN 
CANARD CGCAN .0 III 4 
FUSELAGE CGF . 0 IN 
NOSE LAMBING GEAR CGLGN . 0 IN 4 
MAIN LANDING GEAR Cl . 074 . 0 IN 
TWO FORWARD ;-.!::-TNES CGEP .0 IN 4 
ONE OR TWO AFT .ENGINES CGEA . z IN 
AUXILIARY POWER UNIT CCAP .c IN + 
AVIONICS GflOUF CGAV ,0 IN 
ARMAMMJT GROUP CGARH .D IN 4 
FLIGHT CREW CGCR . ;.J IN 
PA-SMKNUERS. CGP .0 IN 
CARGO/EXT STOKES IN WING CGC'W .0 E[i 
CARGO/EXT STORES IN FUSE .0 IN 
HJBELAi't: FUEL CGZW1 .0 IN 
WTNC FUEL CGFWF . 0 IN 
AIR INDUCTION SYSTEM CON . 0 IH 
AIR CONDITIONING cGAO . 0 IN 
# NAMKI.I.TT SCONFIN 
GEOMETRIC RATIOS, OBJECTIVE FUNCTION FACTORS, AND DESIGN VARIABLES 
OEfCSTPTION NAME 
DESIGN RANGE DESKNG 
WIN!) LOADING REQUIRED WSR 
THRUST/WEIGHT ETKQUMTP TtUR 
OLOVE/WING AREA RECUTHED PGLOV 
HORIl TAIL VOLUME COEF HTVC 
VERT TAIL VOLUME COTF Vi'VC 
COST CALCULATION SWITCH I COST 
3N TO BE K'.'^EO 
ACH'd'/D) + 
4 SI0N3) 
UEcISN V.MUAHLE DATA 
- OBJ -
VARIABLE 
SCALE FACTOR 
NAME 
RAMP WEIGHT, LBF GW 
.OOOOO 
WING ASPECT RATIO AR 
.000DO 
, ..• jSY • !•' ENGINE, LBF I i 
.00000 
REF WING AREA, SQ FT SW 
.0D00O 
WING TAPER RATIO TR 
.00000 
WING 1/4 CHORD SWEEP, DEG SWEEP 
.00000 
WING T/C TCA 
.00000 
CRUISE MACH NUMBER VCMN 
,00000 
MAX CRULSE ALTITUDE, FT CH 
.UUOOC 
TURBINE IM.FT TEMP (R) ETIT 
. 00000 
OVERAI L PRESSURE RATIO EOPR 
. 0DD00 
FAN PRESSURE RATIO EF'PR 
.OOOUO 
BYPASS RATIO KB PR 
.00000 
THROTTLE RATIO LTTJl 
.00000 
VALUE iJlKSNSICNS 
3900.0 N MI 
oo 
ooooo 
ooooo 
1.5399t7 
. 1000OO 
0 
. 000(1* ("AMP WEIGHT) t 1.00WFUEL + .OC 
.0000-1ANGE 4 .0000'COST + . 0000MNOX 
VALUE A'. ' . .. Y LLVLR t •:•> ) C7PEJI T OUNC 
650000.0 
7 .2 000 
4Q7DO.• 
3800.0 
,00000 
25. 00 
. 12200 
.75000 
45000.0 
.00 
. 000 
.0000 
.oooo 
. ooooo 
.0 
.COoo 
.000 
.0 
.ooooo 
.00 
.ooooo 
.00000 
.0 
.00 
.ooo 
.oooo 
.00DO 
.ooooo 
.0 
, OOOO 
. 000 
.0 
.00000 
00 
.ooooo 
. ooooo 
. 0 
.00 
.ooo 
. oooo 
.oooo 
. ooooo 
NAMELIST SAER1N 
AKRCDYMAMIC OPTIONS AND APPP.OXIKATE TAKEOFF AND LANDING DATA 
DESCRIPTION VAJ.UE DIMENSIONS 
AERODYNAMIC INPUT METHOD MYAERO 
WAVE DRAG INPUT SWITCH IWAVE 
WAVE DRAG FACTOR FWAV
LINEAR/PARABOLIC INTERP ITPAER 
AERO MATRIX FORMAT SWITCH IBO 
MAX CAMBER AT 70 PERCENT 
SEMISPAN CAM 
AIRCRAFT BASE AREA SBASE 
WING TECHNOLOGY AITEK 
MODIFY EDET DATA MODARO 
FIXED DESIGN CL FCLDES 
TURBULENT /LAMINAR FLOW XI JAM 
AERO EFFICIENCY FACTOR E 
0 
0 
1.000C 
2 
0 
.00000 PERCENT CHORE 
.0 SQ FT 
i .2 
0 
-1.OOOO 
.0 
1.0000 
OVERRIDE PARAMETERS FOR WETTED AREAS 
WING WETTED AREA SWETW 
HOR. TAIL WETTED AREA SWETH 
VERT. TAIL WETTED AREA SWETV 
FUSELAGE WETTED AREA SWETF 
NACELLE WETTED AREA SWETN 
. oooo oooc oooo oooo oooo 
TAKEOFF AND LANDING DATA 
RATIO OF MAX. LANDING WT. 
TO MAX. TAKEOFF WT. WRATIO 
MAX. LANDING VELOCITY VAPPR 
MAX. TAKEOFF FIELD LENGTH FLTO 
MAX. LANDING FIELD LENGTH FLLDG 
MAX. CL TAKEOFF CONFIG. CLTOW 
MAX. CL LANDING CONFIG. CLLDM 
APPROACH CL CLAPP 
AIR DENSITY RATIO DRATIO 
L/D RATIO 2ND SEG. CLIMB ELODSS 
L/D RATIO MISSED APPROACH ELODMA 
THRUST PER ENGINE TAKEOFF THROFF 
THRUST PER ENGINE 2ND 
SEG. CLIMB THRSS 
THRUST PER ENGINE MISSED 
APPROACH THRMA 
.7075 
115.0000 
4400.0 
3200.0 
3 . 5850 
3.0000 
.0000 
1.0000 
.0000 
.oooo 
,0000 
KTS 
FT 
FT 
. 0 LBF 
. 0 LBF 
H NAMELIST SENGDIN 
ENGINE DECK CONTROL, SCALING AND USAGE DATA 
DESCRIPTION VALUE DIMENSIONS 
ENGINE DECK PRINT CONTROL NGPRT 1 
ENGINE DECK SOURCE SWITCH IGENEN
SLOPE FACTOR FOR 
EXTRAPOLATING FUEL FLOWS EXTFAC 1.0000 
SUBSONIC FUEL FLOW FACTOR FFFSUB 1.0000 
SUPERSONIC FUEL FLOW FACT FFFSUP 1,0000 
FLIGHT IDLE SWITCH IDLE 1 
IGNORE NEGATIVE THRUSTS NONEG
MIN IDLE FUEL FLOW FRACT FIDMIN .0800 
MAX IDLE FUEL FLOW FRACT FIDMAX 1.0000 
SFC EXTRAPOLATION SWITCH IXTRAP - 0 
PART POWER DATA SWITCH IFILL 2 
MAX. CRUISE POWER SETTING MAXCR
BOOST ENGINE SWITCH BOOST .0000 
FUEL FLOW SCALING 
CONSTANT TERM DFFAC ,0000 
FUEL FLOW SCALING 
LINEAR TERM FFFAC . 0000 
NITROGEN OXIDES SWITCH NOX 0 
INSTALLATION DRAG SWITCH INSDRG 0 
-MIDDLE-FLOPS-OUT 
MACH NUMBERS AND ALTITUDES FOR ENGINE DECK GENERATION 
MACH ALTITUDES 
80 -1 
75 -1 
70 -1 
60 -1 
50 -1 
40 -1 
30 -1 
20 -1 
10 -1 
00 -1 
# NAMELIST $ENGINE 
ENGINE CYCLE ANALYSIS INPUT DATA 
DESCRIPTION VALUE DIMENSIONS 
2-COMP SEP FLOW TORBOFAN 
ENGINE CYCLE DEF. FILE 
IENG 
IFILE 
2 
TFNSEP 
COMPONENT MAP TABLES FILE TFILE ENGTAB 
PRINT LEVEL INDICATOR IPRINT 1 
PRINT VIB/ANOPP DATA NPRINT 0 
PRINT LEVEL FOR WEIGHTS IWTPRT 1 
PLOT ENGINE SCHEMATIC IWTPLT 0 
CYCLE ANALYSIS OUTPUT FILE OFILE ENGOUT 
FLAG TO GENERATE A DECK GEKDEK F 
SWITCH FOR WEIGHT CALCS NG1NWT 0 
(0=NONS, 1=ENGINE, 2-1 + INLET, 3=2 +NACELLE 
PART POWER DATA CONTROL ITHROT 
NUMBER OF A/B POINTS NPAB 
NUMBER OF DRY POINTS NPDRY 
PART POWER THRUST CUTOFF XIDLE 
MAX ALLOWABLE ITERATIONS NITMAX 
4=3+NOZZLE) 
1 
0 
15 
.05000 
50 
DESIGN POINT DATA 
DESIGN POINT NET THRUST DESFN 40700.0 
OVERALL PRESSURE RATIO OPRDES 30.8000 
FAN PRESSURE RATIO FPRDES 1.5000 
BYPASS RATIO BPRDES 5.9000 
DESIGN TURBINE INLET TEMP TETDES 2800.0 
DESIGN THROTTLE RATIO TTRPES 1.0000 DEG R 
OTHER ENGINE CONFIGURATION DEFINITION DATA 
FLAG FOR AFTERBURNER ABURN F 
FLAG FOR DUCT BURNER DBURN F 
AFTERBURNER EFFICIENCY EFFAB .85000 
MAX AFTERBURNER TEMP TABMAX 3500.0 DEG R 
FLAG FOR VARIABLE NOZZLE VEN F 
CUSTOMER COMPRESSOR BLEED COSTBL 1.0000 LB/SEC 
TURBINE COOLING (FROM HPC) WCOOL -.0001 FRACTION (OR T41 Rl 
CUSTOMER POWER EXTRACTION HPEXT 200.00 HP 
FUEL HEATING VALUE FHV 18500.0 BTU/LB 
TECHNOLOGY AVAILABILITY YEAR 1995. YEAR 
FLAG TO DO BOATTAIL DRAG BOAT F 
DELTA TEMPERATURE DTCE .00 DEG C 
DTCE VARIES TO ZERO AT ATC 10000. FT 
FLAG TO DO SPILLAGE DRAG SPILL F 
FLAG TO DO LIP DRAG LIP F 
NOT IH 96 15.09:05 
CI7-M1DDLE 
USED TO DEFIHt HACH-ALTITUDE ARSiAV POINTS 
MAXIMUM MACH MUMfiEH XMHAX . 7SQQ ttKilMUM
 ALTITUDE AHAX 43000.0 
INCREMENT IN MACH NUMBER XK,"C .2030 
INCFEKENT IN ALTITUDE AINC 5000.0 
HLNIKOM DYHAMIC PRESSORS QMIN 150.00 
MAXIMUM DYNAMIC PRESSURE UMAX 1200.00 
PSF 
PSF 
ENGINE CYCL2 OPTIMISATION CRUISE COND1'L';ON 
MACH NUMBER XMDES .7500 
ALTITUDE XADES 4 5000.0 FT 
ENCNt CYCLE LE::AVI"Ri CONSTRAINTS 
MAX COMPRINT! DISCHARGE TOP CDTHAX 939i)9.000D R 
MAX COMSTtESR DISCHARGE PRS CD.-MAX 99999 . 0000 P31 
MAX if w JET TOLOCITY VJMAX 93399.0003 -T/SEC 
MINIMUM SPECIFIC THRUST S':"M [N 1 .0000 LB/LB/SEC 
MAXJKM 3YPASS--.-.-.K3 AREA AF.MAX 99999. OOOO 
SEA LEVKL STATIC MAXIMUM THRUST i 3700.0 LB 
GENERATED PROPULSION SYSTEM WT. 7100.0 LB 
(NEW 3ASELINE ENGINE THRUST - OVERRIDES THRSO) 
# ALL POINT ENGlr-jy CHUCK SUMMARY 
HACH = . fiOO, ALTITUDE = 43000.. THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
50U4.B 4405.2 3779.3 3169.7 3159.2 2B5J.9 2535.6 2244.9 1977.3 1730.0 
4 1502.4 1393.9 1J03.2 917.6 142.3 .• 
3182.2 2821.3 2 4 69.9 2331.6 2JR3.B 2025.4 1872.7 1731.9 1631.6 1483.9 
+ 1368.9 1265.0 1138.4 1077.2 991.8 329.3 
.628 .640 .659 .672 .688 .71D .739 .771 .810 .856 
+ .978 1.359 1.174 1.335 000 
MAC!! .333. ALTITUDE - 350DO., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
6447. 4 5603.1 133 1. .7 441 /.2 4034.6 3630.6 3228.0 2857.9 3 2 2202.4 
* 1332.7 1647.2 1404.4 1160.5 945.6 .3 
4554.7 3.7-.1-S.7 3 372,! 2970.8 2778.7 2380.6 2386.0 2206.7 2743.7 1886.8 
+ 1 744.1 16 1 1. 3 1488.7 1272.5 1.263 ,7 851.3 
.629 .63] .659 .673 .639 .731 .739 .772 .811 .857 
+ .912 .978 1.060 1.175 1.336 .000 
MACH = .800, ALTITUDE = 30000., THRUSTS/FUEL ?LOWS/SfCS/NOX RATIOS FOLLOW 
81S3.4 7100.2 6091,4 5592.5 5108.1 4596,6 4086.8 361B.3 71ti 7'.0 2/83.3 
2421.3 2085.5 1778.1 1479.4 1197.2 .0 
5231,2 4653.4 4.H8.7 58S7.4 1591,6 3342.1 3090.1 2857.8 2642.9 2443.6 
2258.* 2587.4 1928.1 1777.5 1636.5 1038.4 
.643 .636 .675 .686 .704 .727 .756 .790 .329 .876 
.933 1.001 1.334 1.2D2 1.367 .000 
MACH = .fl00, ALTITUDE = 25005., THRUSTS/37 3 L FLOWS/SFCS/NOX RATIOS FOLLOW 
10227.4 8395.4 7631,6 7006.5 6399.6 5758.8 3120.1 4533,2 3992.S 3493.3 
1033.9 2612-7 2227.6 1853.4 1499,9 .0 
5710.3 5966.7 i265 9 4131.1 1512.2 4233.5 3960.5 3662.8 3387.3 3131.3 
1895.0 2675.3 2471,3 2276.2 2097.5 1330.9 
.358 ,671 .690 .704 .721 .V4i .774 .608 .848 .897 
.954 1.024 1.109 1.229 1.398 .000 
HACH '0, ALTIT-JL 2OD50. THRUSTS/FJEL FLOWS/SFCS/NOX RATIOS FOLLOW 
12701,3 11047.1 94//.6 8701.3 7947.6 7131.8 6358,6 5629.7 49S.3.6 1333.3 
37C7.7 3244,7 2766.5 2301.7 1362.7 .0 
8550.0 7579,9 6689,7 5254.4 5855.5 5111.7 5031.3 4653.1 4303.1 3978.6 
3677.6 3393.7 3133.2 =894.1 2664.6 1690,B 
.673 .686 ,706 .720 .737 .761 .791 .827 .868 .317 
.976 1.047 1.135 1.257 1.431 .003 
MACH • .BOO, ALTfTUPE - 15053., THRUST:?.'FUEL FLOWS-.SFCS/NOX RATIOS FOLLOW 
15553.7 1361S.O 116BU.6 10723.9 9793.0 0814.2 7636.7 6938.4 6111.2 5346.8 
-FLOPS-OUT 
+ 4613.5 3999.0 1105.6 2836.7 £199.7 .0 
10777.2 9554,4 8432.3 7895.2 7385,5 6359.1 4312.0 5365.2 5121,0 5013,0 
+ 4635.3 4284.0 3957.0 3S43.0 3353.7 2131.2 
.6B8 ,7D2 -722 .716 .754 .778 .35'- -B-IL .'::".' .938 
+ .998 1.07 1.13- 1.236 1.461 .000 
HACH • -300, AI3'ITLIDE * 10000., THRUSTS / FUEL PLOWS/SFtS/NOX RATIOS FOLLOW 
17AR5,7 15556.3 13346.1 12252.9 11191.6 .3371,0 8954.1 7927.7 6982.6 6109.1 
+ 3305.7 4569.2 339 5.7 31311.2 2623.0 .0 
72377 3 11239.4 99IH.4 9263.7 B633.0 3063.8 741J0.4 6899.6 6380.5 5299,5 
+ 545 3.4 31115,5 4654.8 4291.4 3951.1 2507.0 
.709 .723 .745 .758 .776 .851 .313 .373 ,914 .966 
+ 1.028 1.103 1.195 1.324 1.506 .000 
MACH = .800, ALT TUDE = 5030., T7>:ji]S': 3/FUE1, FLOWS/SFCS/NOX RATIOS r'Hj[.T,OW 
13913.5 16150.2 14J13.1 12957.3 11831.8 10619.7 9168.7 8333.2 75fc3.a 6160.2 
+ 5615,3 4333.8 4159.6 3427.5 2773.8 .0 
13954.6 12371.3 10918.4 10224.1 9562.9 BBB1.4 8211.7 7594.4 7023.1 6493.6 
+ 6002.6 5547.0 51.73.3 4723.6 43 4J.0 2759.5 .738 .752 .774 .789 , j'Jii ,334 .867 .906 .951 1.O05 
t 1.070 1.14 b 1.244 1.378 1.56.8 .000 
MACH - .800, ALTITUDE = 0., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
19837.8 17254.1 14302.5 13590.3 12413.1 11170.2 9937.4 8792.9 7744.7 6775.9 
•F 5884.7 b567.9 4320.9 3595.0 2939.3 .0 
15315.2 17577.3 11962.9 11221.0 10495.4 9747.4 9012.4 8334.9 7707.9 7126.7 
+ 6687.8 6087.9 5523.2 S.184 . 1 4773.0 3023.S 
.772 .787 .810 .826 .346 . !:73 .907 .948 .995 1.052 
* 1.119 1.201 1.3' '. 1.442 1.641 .000 
MACH - .750, ALTITUDE = 45355 ., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
4341.1 5295.4 3686.8 3390.3 3133.5 2798.1 2493.4 2212.3 1951.5 17i3.8 
+ 14 99.5 7 283.7 J i5' 3 903.2 735,7 .0 
3006.4 2665.3 2352.4 2201.0 2062.9 1917.2 1773.8 135L.1 1513.1 1404.0 
T 1298.2 1200.0 1108.4 1020.7 939.8 592.0 
.60E .620 .633 .650 .635 .685 ,711 .742 .778 .821 
1 .872 .933 1.007 1.124 1.276 .000 
MACH - .750, ATTITUDE - 35000., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
6290.5 5468.6 4693,7 11L6.9 3951.1 3562.3 3174.4 2316,3 2181,5 217B.1 
+ 1896.3 1B3B.2 !. ,9 1156.2 937.9 .0 
3829.8 3395.3 2996.7 2557.7 262:;.3 2442.3 2259.6 2033.6 1933.9 1788.6 
+ 1653.3 1523.6 1412.0 1300.3 1197.2 754.2 
.609 .621 ,638 .650 .535 .686 .712 .742 ,773 .821 
+ .872 .35 7 1.008 1.7 23 1.276 .000 
MACH - .760, ALTITUDE = 30000., TBEUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
7964.6 6923.9 5942.9 5465.7 5D02.fi 4510.4 4019.2 3566.2 3145.7 2757.7 
+ 2401.0 20"'4.1 1773.7 1433."' 1187.3 .0 
4959.7 1357.0 3883.3 3636.1 3403.3 3IH3.8 2926.3 2707.4 2504.5 2316.3 
+ 2141.7 1979,5 1823.5 1633.9 1350.4 976.7 
.623 .635 .553 .665 .630 .741 .728 .759 .796 ,B40 
+ .892 .954 1.537 1.150 1.335 ,300 
MACH = .750, ALTITUDE = 2SOOO., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
9474.0 8674,2 7115.1 $847.3 6267.2 5650.5 5035.2 445:.6 3540.3 3454.8 
<r 3007.9 2598.4 2222.0 1853.9 1487.7 ,0 
6355.7 5634.6 1973.1 -1659.5 3737 7. 4053.0 3749.9 3 :59.4 3259.4 2968.2 
+ 2714.5 2536.8 2343.2 2157.9 1986.3 1251.5 
.637 .650 .468 .650 ,596 .717 .745 .777 .814 .855 
+ .912 .976 1.GS5 1.177 1.333 .000 
MACH = .753, ALTITUDE = ..'•'.'-•0., THRUSTS/FUEL FLOW.- ,'FFCK 'NOX RATIOS FOLLOW 
12386.2 10769.4 9213.5 3501.3 7781.0 7515.5 6251.5 5516.3 1892.9 4239.3 
+ 3711.5 .1226.1 275B.6 2276.9 1847,1 .5 
8070.8 7155.1 6315.1 S916.3 553B.1 5146.7 4761.3 1405.7 1075.1 3759.2 
+ 3495.1 3221.4 2975.5 2713.2 2522.9 1533.3 
Nov IS 96 
15:09:05 C17-
.651 .664 .683 .696 .712 .734 .762 .794 .833 .879 
.933 .999 1.079 1.203 1.366 .000 
MACH = .750, ALTITUDE = 15000., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
1S263.4 13269.0 11388.9 10474.4 9587,0 8643.7 7702.4 6834.2 6028.5 5284.9 
4601.3 3974.8 3399.L 2805.4 2275.7 .0 
10169.0 9015.2 7956.8 7455.1 6977.8 6484.7 5999.8 5551.0 5134.9 4749.1 
4391.2 4058.8 3749.1 3452.6 3178.8 2002.4 
.666 .679 .699 .712 .728 .750 ,779 .812 .852 .899 
.954 1.021 1.103 1.231 1.397 .000 
MACH = .750, ALTITUDE = 10000., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
18359.2 15960.2 13698.8 12598.9 11531.4 10396.8 9264.7 8220.3 7251.2 6356.8 
5534.5 4781.0 4088.5 3374.4 2737.3 ,0 
12525.0 11103.9 9800.3 9182.3 8594.5 7987.2 7389.9 6837,1 6324,6 5849.4 
5408.5 4999.2 4617.7 4252.5 3915.3 2466.4 
,682 .696 .715 .729 .745 .768 .798 .832 .872 .920 
.977 1.046 1.129 1.260 1.430 .000 
MACH = .750, ALTITUDE = 5000., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
19452.9 16911.0 14514.9 13349.5 12218.4 11016,2 9816.6 8710.0 7683.2 6735.5 
5864.3 5065.9 4332.1 3575.4 2900.4 ,0 
13784.7 12220.7 10785.9 10105.9 9458.9 8790.5 8133.1 7524.8 6960.7 6437,7 
5952.S 5502.0 5082.1 4680.2 4309.1 2714.4 
.709 .723 .743 .757 .774 ,798 .829 .864 .906 .956 
1.015 1.086 1.173 1.309 1.486 .000 
MACH = .750, ALTITUDE - 0., THRUSTS/FUEL PLOWS/SFCS/NOX RATIOS FOLLOW 
20470.4 17795.5 15274.0 14047.7 12857.3 11592.4 10330.0 9165.6 8085.0 7087.8 
6171.0 5330.8 4558.7 3762.4 3052.1 .0 
15127.5 13411.0 11836.6 11090.2 10380.2 9646.7 8925.3 8257.7 7638.7 7064.8 
6532.3 6037.9 5577.2 5136.0 4728.8 2978.8 
.739 .754 .775 .789 .807 ,832 .864 .901 .945 .997 
1.059 1.133 1.223 1.365 1.549 .000 
MACH = .700, ALTITUDE = 35000., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
6166.7 5374,1 4634.6 4275.4 3922.3 3542.8 3167.0 2817.0 2492.5 2193.2 
1918.0 1665.6 1415.4 1174.2 956.5 .0 
3628.4 3217.6 2844.6 2665.9 2495.2 2317.6 2144.0 1982.9 1833.6 1695.0 
1566.5 1447.0 1333.7 1227.2 1128,0 692.5 
.588 .599 .614 .624 .636 ,654 .677 .704 .736 .773 
.817 .869 .942 1.045 1.179 .000 
MACH = .700, ALTITUDE = 3OO00., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
7807.7 6804.1 5867.9 5413.0 4966.0 4485.6 4009.8 3566.6 3155.8 2776.8 
2428.4 2108.8 1792.0 1436.7 1211.0 .0 
4698.3 4166.4 3683.3 3452.0 3230.9 3001.0 2776,2 2567.6 2374.2 2194.9 
2028.5 1873,7 1726.9 1589.0 1460.6 896.7 
.602 .612 .628 .638 .651 .669 .692 .720 .752 .790 
.835 .889 ,964 1.069 1.206 .000 
MACH ^ .700, ALTITUDE = 25000., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
9731.4 8524.2 7351.3 6781.5 6221.4 5619.5 5023.4 4468.2 3953.6 3478.8 
3042.3 2641.9 2245.0 1862.5 1517.1 .0 
6020.4 5338.9 4719.8 4423.5 4140.1 3845.5 3557.4 3290.1 3042.3 2812.5 
2599.3 2401.0 2212.9 2036.2 1871.7 1149.0 
.615 .626 .642 .652 .665 .684 .708 .736 .770 .808 
.854 .909 .986 1.093 1.234 .000 
MACH = .700, ALTITUDE = 20000., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
12141.8 10531.1 9125.2 8417,9 7722.7 6975.5 6235.6 5546.4 4907.6 4313.2 
3776.4 3279.4 2786,8 2311.9 1883.2 .0 
7642.7 6777.5 5991.7 5615.4 5255.8 4881.8 4516.0 4176.7 3862.1 3570.4 
3299.7 3048.0 2809.2 2584.9 2376.0 1458.6 
.629 .641 ,657 .667 .681 .700 .724 .753 .787 .827 
.874 .929 1.008 1.118 1.262 .000 
FLOPS-OUT 
MACH = .700, ALTITUDE = 15000., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
14954.8 13032.5 11239.4 10368.1 9511.8 8591,6 76B0.3 6831.4 6044.6 5318.7 
4651.3 4039.2 3432.4 2847.5 2319.5 .0 
9625.3 8535.7 7546.0 7072,2 6619.2 6148.2 5687.5 5260.2 4864.0 4496.6 
4155.7 3838.6 3538.0 3255.5 2992.4 1837.0 
.644 .655 .671 .682 .696 .716 .741 .770 .805 ,845 
.893 .950 1,031 1.143 1.290 .000 
MACH = ,700, ALTITUDE = 10000,, THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
18287.1 15936.5 13743.8 12678.4 11631.3 10506.1 9391.7 8353.7 7391.5 6503.8 
5687.8 4939.3 4197.2 3482.1 2836,3 .0 
12032.7 10670.6 9433.4 8841.0 8274.8 7685.9 7110.0 6575.9 6080.6 5621.3 
5195.1 4798.7 4422.9 4069.7 3740.9 2296.5 
.658 ,670 .686 .697 .711 .732 .757 .787 .823 .864 
.913 .972 1.054 1.169 1.319 .000 
MACH = .700, ALTITUDE = 5000., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
20066.7 17487.3 15081.2 13912.2 12763.2 11528.4 10305.6 9166.6 8110.8 7136.7 
6241.3 5419.9 4605.7 3820.9 3112.3 .0 
13629.5 12086.6 10685.2 10014.2 9372.8 8705.9 8053.5 7448.5 6887.5 6367.2 
5884.5 5435.5 5009.8 4609.7 4237.3 2601.2 
.679 .691 .709 .720 .734 .755 .781 .813 ,849 .892 
.943 1.003 1.088 1.206 1.361 .000 
MACH = .700, ALTITUDE * 0., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
21196.2 18471.7 15930,2 14695.3 13481.6 12177.4 10885.7 9682.6 8567.4 7538.5 
6592.6 5725.0 4864.9 4036.0 3287.5 .0 
14960.7 13267.1 11728.8 10992.3 10288.3 9556.2 8840.1 8176.0 7560.2 6989.1 
6459.2 5966.4 5499.1 5060.0 4651.1 2855.3 
.706 .718 .736 .748 .763 .785 .812 .844 .882 .927 
.980 1.042 1.130 1.254 1.415 .000 
MACH = .600, ALTITUDE = 30000., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
7718.9 6780.6 5898,1 5443.6 5010.5 4535.4 4067.4 3629.5 3219.0 2841.2 
2494.1 2128.5 1782.4 1472,0 1196.9 .0 
- 4290.4 3812.0 3375.9 3154.9 2946.1 2726.2 2514.0 2317.2 2134.4 1965.2 
1808.4 1657,8 1517.4 1387.7 1268.6 750.4 
.556 .562 .572 .580 ,588 .601 .618 .63B ,663 .692 
.725 .779 .851 .943 1.060 .000 
MACH = .600, ALTITUDE = 25000., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
9670.4 8494.8 7389.2 6319.8 6277.1 5682.0 5095.7 4547.0 4032.8 3559.5 
3124.7 2666.6 2233.0 1344.1 1499.5 .0 
5498.0 4884.9 4326.1 4042.9 3775.3 3493.5 3221.6 2969.3 2735.1 2518.4 
2317.3 2124,4 1944.5 1778.2 1625.6 961.6 
.569 .575 .585 .593 .601 .615 .632 .653 .678 .708 
.742 .797 .871 .964 1.084 .000 
MACH = .600, ALTITUDE - 20000., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
12001.5 10542.5 9170.5 8463.3 7790.3 7051.7 6324.1 5643.2 5005.0 4417.6 
3877.9 3309.4 2771.3 2288.7 1861.0 .0 
6978.0 6199.9 5490.7 5131.2 4791.5 4434.0 4088.8 3768.7 3471.3 3196.3 
2941.1 2696.2 2467.9 2256.9 2063.2 1220.4 
.581 .588 .599 .606 .615 .629 .647 .668 .694 .724 
.758 .815 .891 .986 1.109 .000 
MACH = .600, ALTITUDE - 15000., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
14773.5 12977.5 11288.5 10418.6 9589.6 8680.4 7784.7 6946.6 6161.0 5437.9 
4773.6 4073.8 3411.4 2817.3 2290.8 .0 
8782.4 7803.1 6910.5 6458.1 6030.6 5580.6 5146.1 4743.2 4369.0 4022.8 
3701.7 3393.5 3106.1 2840.5 2596.7 1536.0 
.594 .601 .612 .620 .629 .643 .661 .683 .709 .740 
.775 .833 .911 1.008 1.134 .000 
MACH a .600, ALTITUDE = 10000., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
18055.3 15860.3 13796.2 12733.0 11719.9 10608.7 9514.0 8489.6 7529.6 6645.9 
5834.0 4978.7 4169.2 3443.1 2799.7 ,0 
15:09:05 C17-
10971.8 9743.'! 8633.3 8068.0 7533.9 6971.7 6429.0 5925.7 5458.2 5025.7 
+ 4624.5 4239.4 3880.4 3548.6 3244.1 1913.9 
.608 .615 .626 .634 .643 .657 .676 .698 .725 .756 T
 .793 .852 .931 1.031 1.159 .000 
MACH = .600, ALTITUDE = 5000., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
21508.6 18893.9 16434.9 15168.4 13961.5 12637.8 11333.7 10113.4 8969.7 7917.0 
+ 6949.9 5931.0 4966.6 4101.7 3335.2 .0 
13368.8 11878.0 10519.3 9830.6 9179.8 3494.8 7833.5 7220.2 6650.6 6123.6 
+ 5634.8 5165.6 4728.1 4323.9 3952.8 2338.2 
.622 .629 .640 .648 .653 .672 .691 .714 .741 .773 
<- .811 .871 .952 1.054 1.185 .000 
MACH = .600, ALTITUDE = 0., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
22932.0 20144.2 17522.5 16172.2 14885.4 13474.1 12083.7 10782.7 9563.3 8440.9 
T 7409.8 6323.5 5295.3 4373.1 3555.9 .0 
14692.6 13054.2 11561.0 10804.0 10088,9 9336.0 3609.2 7935.2 7309.1 6730.0 
+ 6192.7 5677.1 5196.3 4752.0 4344.2 2569.7 
.641 .648 .660 .668 .678 .693 .712 .736 .764 .797 
+ .836 .898 .981 1.087 1.222 .000 
MACH ,500, ALTITUDE 20000. THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
12279.6 10898.4 9607,3 8876.8 8171.1 7390.0 
4047.4 3447.9 2878.4 2371.0 1917.6 .0 
6523.6 5808.6 5156.8 4797.4 4456.8 4098.6 
2628.9 2391.2 2169.8 1967.0 1780.6 992.1 
.531 .533 .537 .540 .545 .555 
.650 .694 .754 .830 .929 .000 
6628.2 5922.0 5270.0 4669.2 
3756.5 3441,5 3151.4 2883.4 
.567 .581 .598 .618 
MACH .500, ALTITUDE = 15000., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
15110.5 13410.3 11822.1 10923.2 10O54.8 9093.6 
4980.5 4242.8 3542.0 2917.6 2359.7 .0 
8207.6 7308.0 6488.0 6035.8 5607.3 5156.6 
3307,5 3008.4 2729.9 2474.8 2240.2 1248.2 
.543 .545 .549 .553 .558 .567 
.664 ,709 .771 .848 .949 .000 
8156.2 7287,2 6484.9 5745.6 
4726.2 4329.9 3964.9 3627.8 
.579 .611 . 631 
MACH = .SO0, ALTITUDE 10000. THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
18456.3 16380.3 14439.7 13341.9 12281.1 11107.1 
6083.2 5182,3 4326.2 3563.7 2882.2 .0 
10247.5 9124.4 8100.5 7535.9 7000.9 6438.2 
4129,6 3756.2 3408.3 3089.8 2797.0 1558.5 
-555 -557 .561 .565 .570 .580 
.679 ,725 .788 .867 .970 .000 
9962.2 8900.8 7920.8 7017.8 
5900.8 5406-0 4950.3 4529.4 
.592 .607 .625 .645 
MACH = ,500, ALTITUDE = 5000., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
22387.6 19869.3 17515.5 16183.7 14397.1 13473.0 12084.2 10796.7 9608.0 8512.6 
+ 7379.0 6286.1 5247.7 4322.8 3496.1 .0 
12703.7 11311.4 10042.1 9342.2 8679.0 7981.4 7315.2 6701.8 6136.8 5615.1 
* 5119.4 4656.5 4225.3 3830.5 3467,4 1932.0 
.567 .569 .573 .577 .583 .592 .605 .621 .639 .660 
+ .694 .741 .805 .886 .992 .000 
MACH = .500, ALTITUDE = 0., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
24956.3 22149.2 19525.2 18040.7 16606.4 15018.9 13470.7 12035.5 10710.5 9489.3 
<• 8225.7 7007.4 5849.9 4818.8 3897.2 .0 
14480.5 12893.5 11446.7 10648.9 9892.9 9097.8 8333.4 7639.1 6995.1 6400.5 
+ 5835-4 5307.8 4816.3 4366.2 3952.4 2202.2 
.580 .582 .586 .590 .596 .606 .619 .635 .653 .674 
+ ,709 .757 .823 .906 1.014 .000 
MACH = .400, ALTITUDE = 1000O,, THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
19388.6 17374.6 15462.0 14297.1 13170.0 11919.3 10704.3 9577.1 8534.5 7486.4 
6438.2 5489.0 4620.9 3793.9 2974.1 .0 
9759.2 8703.1 7734.3 7157,0 6612.0 6040.5 5498.7 5001.8 4545.3 4117.7 
3717.1 3351.0 3014.8 2703.8 2397.4 1285.7 
.503 .501 .500 .501 .502 .507 .514 .522 .533 .550 
+ .577 .610 .652 .713 .306 .000 
MACH = .400, ALTITUDE = 5000., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
23508.6 21066.6 18747.6 17335.2 15968.6 14452.1 12978.9 11612.2 10348.0 9077.2 
+ 7806.3 6655.4 5602.8 4600.0 3606.1 .0 
12093.9 10785.1 9584.6 8869.2 8193.8 748S.5 6814.2 6198.4 5632.7 5102.8 
+ 4606.3 4152.6 3736.0 3350.6 2970.9 1593.3 
.514 .512 .511 .512 .513 .518 .525 .534 .544 .562 
+ .590 .624 ,667 .728 .824 .000 
MACH = .400, ALTITUDE = 0,, THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
27298.1 24462.5 21769.7 20129.6 18542.7 16781.7 15071.1 13484,1 12016.1 10540.5 
4- 9064.6 7728.2 6506.0 5341.5 4187.4 .0 
14316.7 12767.4 11346.2 10499.3 9699.7 8861.3 3066.6 7337.6 6668.0 6040.6 
+ 5453.0 4915.9 4422.7 3966.5 3517.0 1886,1 
.524 ,522 .521 .522 .523 .528 .535 .544 ,555 .573 
+ .602 .636 .680 .743 .840 .000 
MACH = .300, ALTITUDE = 5000., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
25221.8 22780.4 20475,9 18952.7 17477.0 15844.1 14241.2 12748.9 11289.8 9328.3 
4- 8497.4 7262.9 6113.1 5047.1 3865.9 .0 
11717.0 10457.3 9303.6 8565.0 7869.8 7146,8 6460.9 5833.8 5253.4 4713.4 
+ 4222.2 3772.6 3360.8 2978.2 2583.2 1290.2 
.465 .459 .454 .452 .450 .451 .454 .458 .465 .480 
t .497 .519 .550 .590 .668 .000 
MACH = .300, ALTITUDE = 0., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
29925.9 27029.1 24294.9 22487.5 20736.6 18799.2 16897.3 15126.7 13395.4 11661.4 
+ 10082.2 8617.5 7253.3 5988.4 4586.9 .0 
14181.3 12656.7 11260.3 10366.3 9524.9 8649.9 7819.7 7060.8 6358.3 5704.8 
+ 5110.2 4566.0 4067.7 3604.6 3126.4 1561.6 
.474 .468 .463 .461 .459 .460 .463 .467 .475 .489 
+ .507 .530 .561 .602 .682 .000 
MACH = .200, ALTITUDE = 5000., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
27500.8 25037.4 22681.3 20972.5 19316.9 17487.4 15698.9 14033.7 12320.6 10738.9 
+ 9250,9 7887.4 6650.8 5293.1 3997.4 ,0 
11508.8 10281.6 9152.3 8369.9 7636.9 6879.8 6166.8 5519.7 4917.3 4371,7 
+ 3874.7 3423.4 3014.4 2597.6 2220.9 1058.6 
.418 .411 .404 .399 .395 .393 .393 .393 .399 .407 
* .419 .434 .453 .491 .556 .000 
MACH = .200, ALTITUDE = 0., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
32951.1 29999.5 27176.4 25129.0 23145.3 20953.1 18810.2 16821.0 14762.4 12867.2 
+ 11084.3 9450.6 7968.9 6342.1 4789.7 .0 
14080.4 12579.0 11197.4 10240.1 9343.4 8417.1 7544.8 6753.1 6016.1 5348.6 
*• 4740.5 4188.4 3687.9 3178,0 2717.1 1295,2 
.427 .419 .412 .408 .404 .402 .401 ,401 .408 .416 4-
 .428 .443 .463 .501 .567 .000 
MACH = .100, ALTITUDE = 5000., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
30350.4 27786.1 25342.0 23469.4 21650.2 19624.5 17640.2 15716.2 13786.2 12025.3 
4- 10391,6 8896.4 7409.2 5734.9 4429.6 .0 
11408.3 10192.8 9075.9 8258.4 7495.0 6707.9 5971.3 5299.8 4683.3 4130.5 
4- 3629.4 3178.8 2750.0 2330.0 1968.8 912.7 
.376 .367 .358 .352 .346 .342 ,339 .337 .340 .343 4-
 ,349 .357 .371 .403 .444 .000 
MACH = .100, ALTITUDE = 0., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
36489.0 33406.0 30467.6 28216.2 26029.1 23593.7 21208.0 18894.9 16574.5 14457.5 
4- 12493.4 10695.7 8907.8 6954.9 5325.6 .0 
14016.5 12523.1 11150.9 10146.4 9208.5 8241.5 7336.4 6511.4 5754.0 5074.8 
+ 4459.1 3905.5 3378.8 2862.7 2418.9 1121.3 
.384 .375 .366 .360 .354 .349 .346 .345 .347 .351 4-
 .357 .365 .379 .412 .454 .000 
MACH = .000, ALTITUDE = 5000., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
Nov 18 96 
15:09:05 C17-MIDDLI 
33824.6 31141.5 28571.9 26468.4 24422.6 22105.5 19879.3 17675.0 15512.9 13534,5 
11702.1 10019.1 8071.8 6342.6 4892.9 .0 
11377.9 10166.9 9052,8 8186.1 7380.5 6545.0 5779,4 5083.5 4452.1 3888.9 
3382.8 2928.0 2465.9 2065.1 1721.9 910.2 
.336 .326 .317 .309 .302 .296 .291 .288 .287 ,287 
.2B9 ,292 .305 .326 .352 .000 
MACH = .000, ALTITUDE = 0., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
40700.0 37471.4 34379.6 31848.5 29386.8 26598.8 23920.0 21267.7 18666.1 16285.5 
14080.8 12055.6 9712.5 7631.9 5887.5 .0 
13995.6 12505.9 11135.6 10069.4 9078.6 8050.8 7109.0 6253.1 5476.4 4783.6 
4161.0 3601.6 3033.2 2540.3 2118.0 1119.7 
.344 .334 .324 .316 ,309 .303 .297 .294 .293 .294 
.296 .299 .312 .333 .360 .000 
H REVISED PROPULSION SYSTEM DATA 
BASELINE ENGINE THRUST THRSO 40700.0 LBF 
BASELINE ENGINE WEIGHT WENG 7100.0 LBF 
BASELINE INLET WEIGHT WINL .0 LBF 
BASELINE NOZZLE WEIGHT WNOZ 0 LBF 
BASELINE NACELLE LENGTH XNAC 12.23 FT 
BASELINE NACELLE DIAMETER DNAC 6.23 FT 
# NAMELIST SMISSIN 
PERFORMANCE CONTROLS AND FACTORS AND MISSION SEGMENT DEFINITION 
DESCRIPTION NAME VALUE DIMENSIONS 
ENDURANCE MISSION SWITCH INDR 0 
OVERALL FUEL FLOW FACTOR FACT 1 .0000 
CDO FACTOR FCDO 1 .oooo 
CDI FACTOR FCDI 1 .oooo 
SUBSONIC CD FACTOR FCDSUB 1 .oooo 
SUPERSONIC CD FACTOR FCDSUP 1 .0000 
ENGINE SCALING SWITCH ISKAL 1 
OWE FACTOR OWFACT 1 .oooo 
PRINT FLAG I FLAG 2 
DETAILED MISSION PRINT MSUMPT 1 
TEMPERATURE DEVIATION DTC ,0 DEG C 
CALC RAMP WT OR RANGE IRW 1 
RANGE TOLERANCE RTOL .0010 N MI 
ATA TRAFFIC ALLOWANCE IATA 0 
WEIGHT INCREMENT DWT 1. LBF 
WUND OPERATIONS AND TAKEOFF INPUT 
TAKEOFF TIME TAKOTM 2 . 0 MIN 
TAXI-OUT TIME TAXOTM 15 .0 MIN 
APPROACH TIME APPRTM .0 MIN 
APPROACH FUEL FLOW FACTOR APPFFF 2 .00 
TAXI-IN TIME TAXITM 2 . 0 MIN 
TAKEOFF POWER SETTING ITTFF 1 
TAXI FUEL FLOWS WILL BE FROM THE ENGINE DECK 
INPUT FOR 1 CLIMB SCHEDULES 
MINIMUM CLIMB MACH NUMBER CLMMIN 
MAXIMUM CLIMB MACH NUMBER CLMMAX 
MINIMUM CLIMB ALTITUDE CLAMIN 
FT 
MAXIMUM CLIMB ALTITUDE CLAMAX 
FT 
NUMBER OF CLIMB STEPS NINCL 
CLIMB OPTIMIZATION FACTOR FWF 
FOLLOWING CRUISE SEGMENT NCRCL 
(1) 
.3000 
. 0000 
0. 
0 . 
31 
. 0000 
1 
(2) 
.3000 
. oooc 
0 . 
0. 
31 
.ooio 
1 
(3) 
.3000 
, oooo 
0. 
31 
.0010 
1 
14) 
.3000 
.oooo 
0 . 
0. 
31 
-.ooio 
1 
FLOPS-OUT 
DRAG COEFFICIENT INCREMENT CLDCD .00000 ,00000 .00000 .00000 
NO. OF POWER SETTINGS IPPCL 1111 
STORE DRAG DURING CLIMB ISTCL OOOC 
MAX CLIMB POWER SETTING MAXCL 1 
FAA CLIMB ENFORCED IFAACL C 
FAA DESCENT ENFORCED IFAADE 0 
MINIMUM CLIMB RATE SWITCH NODIVE
MINIMUM CLIMB RATE DIVLIM 0, FT/MIN 
Q LIMIT IN CLIMB QLIM .0 PSF 
MAXIMUM RATE OF DESCENT RDLIM -99999.0 FT/MIN 
INPUT FOR 1 CRUISE SCHEDULES (1) (2) (3) (4) 
(5) (6) 
CRUISE OPTION SWITCH IOC 2 111 
1 1 
CRUISE OPT FUEL FACTOR FFUEL 1.000 1.000 1.000 1.000 
1.000 1.000 
CRUISE OPT NOX FACTOR FNOX .000 .000 .000 .OOC 
.000 .000 
MAXIMUM MACH NUMBER CRMACH .7500 .0000 .0000 .0000 
.0000 .0000 
MAXIMUM ALTITUDE CRALT 28000. -1. -1. -1. 
-1. -1. FT 
DRAG COEFFICIENT INCREMENT CRDCD .00000 .00000 ,00000 .00000 
.00000 .00000 
STORE DRAG DURING CRUISE ISTCR 0 0 0 0 
0 0 
LONG RANGE CRUISE FACTOR FLRCR 1.000 1,000 1.000 1.000 
1.000 1.000 
MINIMUM MACH NUMBER CRMMIM .3000 .0000 .0000 .0000 
.oooo .oooo 
MAXIMUM LIFT COEFFICIENT CRCLMX .0000 ,0000 .0000 .0000 
.0000 .0000 
ENGINE FEATHERING ALLOWED IFEATH 0 0 0 0 
0 0 
ENGINE FRACTION REMAINING FEATHF .5000 .5000 .5000 ,5000 
.5000 .5000 
CD INCREASE FOR FEATHERING CDFETH .00000 .00000 .00000 .00000 
.00000 .00000 
MINIMUM CRUISE ALTITUDE HPMIN 1000. 1000. 1000. 100O. 
1000. 1000. FT 
INCREMENT IN CRUISE WT. DCWT 1.0 LBF 
RATE OF CLIMB CEILING RCIN 100.0 FT/MIN 
INPUT FOR DESCENT SCHEDULE 
DESCENT OPTION SWITCH IVS 
DESCENT LIFT COEFF, DECL 
MINIMUM DESCENT MACH NO. DEMMIN 
MAXIMUM DESCENT MACH NO. DEMMAX 
MINIMUM DESCENT ALTITUDE DEAMIN 
MAXIMUM DESCENT ALTITUDE DEAMAX 
NUMBER OF DESCENT STEPS NINDE 
DRAG COEFFICIENT INCREMENT DEDCD 
STORE DRAG DURING DESCENT ISTDE 
1 
.8000 
.3000 
.0000 
0. 
0 . 
31 
. ooooo 
0 
FT 
FT 
RESER77E SEGMENT INPUT 
RESERVE CALC. OR CONST IRS 
RESERVE FUEL RESRFU 
FRACTION OF TRIP FUEL RESTRP 
MISSED APPROACH TIME TIMMAP 
RANGE TO ALTERNATE AIRPORT ALTRAN 
RESERVE CLIMB SCHEDULE NCLRES 
RESERVE CRUISE SCHEDULE NCRRES 
START RESERVE MACH NUMBER SREMCH 
END RESERVE MACH NUMBER EREMCH 
START RESERVE ALTITUDE SREALT 
END RESERVE ALTITUDE EREALT 
.000 LBM 
.000 
2.0 MIN 
500,0 N MI 
1 
1 
.3000 
,3000 
0. FT 
0 . FT 
Nov 18 96 
15:09:05 
RESERVE HOLDING TIME 
HOLD CRUISE SCHEDULE 
HOLD POSITION SWITCH 
CRUISE ONLY SWITCH 
2ND RES HOLD TIME OR FRAC 
THOLD CRUISE SCHEDULE 
HOLDTM 
NCRHOL 
IHOPOS 
ICRON 
THOLD 
NCRTH 
C17-MIDDLE-FLOPS-OUT 
.0 MIN 
1 
1 
0 
.000 MIN 
1 
it MISSION SEQUENCE DEFINITION 
START 
CLIMB 
CRUISE 
RELEASE 
REFUEL 
CRUISE 
DESCENT 
END 
MACH NUMBER = .3000 
USE CLIMB SCHEDULE 1 
USE CRUISE SCHEDULE I 
PAYLOAD WEIGHT = 112000.0 LB 
FUEL ADDED = -2000.0 LB 
USE CRUISE SCHEDULE 1 
ALTITUDE = 0. FT 
END CRUISE DISTANCE = 3400.0 N MI 
TIME REQUIRED =105.0 MIN 
END CRUISE DISTANCE = 500.0 N MI 
MACH NUMBER ,3000 ALTITUDE = 
fTITLE, BEGIN OUTPUT OF RESULTS 
15000. 
-.00221 
20000. 
-.00194 
25000. 
-.00164 
30000. 
-.00133 
35000. 
-.00099 
40000, 
-.00052 
45000. 
.00000 
50000. 
.00055 
55000. 
.00113 
60000. 
.00175 
-.00310 
-.00219 
-.00272 
-.00192 
- .00231 
-.00163 
-.00187 
-.00131 
-.00140 
-.00098 
- .00074 
- .00052 
.00000 
.00000 
.00079 
.00054 
.00162 
.00112 
.00251 
.00173 
DRAG POLARS 
-.00281 
.00217 
-.00246 
.00190 
-.00209 
.00161 
- . 00169 
.00130 
-.00126 
.00097 
-.00067 
. 0O051 
.00000 
. ooooo 
.00071 
. 00054 
.00146 
,00111 
.00226 
. 00171 
-.00262 
-.00230 
-.00195 
-.00158 
-.00117 
-.00062 
.00000 
.00066 
.00135 
.00209 
-.00248 
-.00218 
-.00185 
-.00149 
-.00111 
-.00059 
.00000 
.00062 
.00128 
.00197 
- .00237 
• .00208 
• .00176 
-.00142 
-.00106 
- .00056 
.00000 
.00059 
.00122 
.00188 
.00228 
.00199 
.00169 
.00137 
.00101 
.00054 
.00000 
.00057 
.00116 
.00180 
-.00225 -.00223 
-.00197 -.00196 
-.00167 -.00166 
-.00135 -.00134 
-.00100 -.00100 
-.00053 -.00053 
, ooooo .ooooo 
.00056 
.00115 
.00178 
.00056 
.0O114 
.00176 
ALTITUDE - 45000. FT 
C17 Short Mission 
+ .500 
,050 
. 550 
. 10C 
.600 
.150 
. 65C 
,200 
.700 
.250 .300 
.750 
.3 50 .400 .450 
FINAL ANALYSIS 
+ 
.200 
03416 
,01982 
.03832 
.01984 
04314 
.02027 
04842 
,02111 
05527 
.02235 .02390 
06357 
.02577 , 02781 03068 
., AERODYNAMIC DATA 
+ 
.300 
03286 
.01852 
.03702 
.01854 
04184 
.01897 
04712 
.01981 
05397 
.02105 .02261 
06228 
.02447 .02651 02939 
MACH NUMBER ALTITUDE REFERENCE AREA TECHNOLOGY LEVEL ,400 .01763 .01765 .01808 .01892 .02016 .02172 .02359 .02563 02850 
.75 4 5000. FT 3800.00 SQ FT 1 .20 4 03197 ,03613 04095 04624 05308 06139 
.500 .01693 ,01696 .01739 .01822 ,01947 ,02102 .02290 .02496 02781 
COMPONENT SWET LENGTH FINENESS FORM RN CF + 03127 ,03543 04026 04554 05238 06069 
CDF . 600 .01670 .01673 .01716 .01799 ,01923 .02080 . 02268 .02477 02760 
SQ FT FT RATIO FACTOR MILLIONS + 03104 .03520 04003 04531 05215 06046 
WING 5819 15 23 25 . 1210 1 . 440 26.3 .002 .700 .01692 .01686 .01725 .01811 .01942 .02101 .02291 .02499 02772 
42 .00533 4 03113 .03531 04012 04540 05223 06054 
HORIZONTAL TAIL 1717 80 13 00 .0850 1 .305 14 .7 . 002 ,725 .01706 .01697 .01736 .01822 .01955 .02116 . 02307 .02517 02785 
65 .00156 + 03127 .03544 04022 04547 05228 O6058 
VERTICAL TAIL 806 95 19 88 .1100 1.398 22 .5 .002 .750 .01742 .01724 .01759 .01847 .01987 .02152 .02341 .02555 02828 
48 .00074 4 03174 .03619 04098 04604 05261 06063 
FUSELAGE 803 6 68 159 10 7 .2220 1 .233 179 . 9 .001 .775 ,01816 .01782 .01811 ,01902 .02056 .02228 . 02420 .02645 02982 
83 .00477 4 03399 .03882 04389 04920 05545 06255 
NACELLE 213 34 12 23 1 .9631 2 . 663 13.8 .002 .800 .01980 .01925 .01947 .02046 .02222 .02417 ,02627 .02926 03346 
67 .00040 4 03797 .04331 04903 05470 06092 06746 
NACELLE 213 34 12 . 23 1 .9631 2
 ,663 
13 .8 .002 . 825 .03497 .03355 .03337 .03447 .03683 .03990 ,04368 .04859 05348 
67 .00040 4 05902 .06529 07117 07735 08368 09009 
NACELLE 213 34 12 . 23 1 ,9631 2 . 663 13.8 .002 
67 .00040 DESIGN MACH NUMBER = .771, DESIGN CL = .458 
NACELLE 213 34 12 . 23 1 .9631 2 . 663 13 . 8 ,002 
67 .00040 MACH CDF CDC BUFFET CL 
MISCELLANEOUS 
.00084 .200 
.30C 
.01906 
.01776 
.00000 
.00000 
1.0S1 
. 996 
TOTAL 17233 94 .003 . 400 .01687 .00000 .919 
27 .01484 .500 
. 600 
,01618 
.01559 
.ooooo 
.00035 
.831 
, 749 
CHANGE IN DRAG COEFFICIENT FROM CRUISE ALTITUDE .700 .01508 .00097 . 640 
ALTITUDE MACH NUMBER .725 .01496 .00119 . 603 
.200 .300 .400 . 500 . 600 .700 .725 .750 ,750 .01484 .00155 .562 
.775 .800 .825 .775 .01472 .00217 . 516 
0. -.00409 -.00372 - 00347 - .00329 - .00315 -.00302 -.00299 - .00296 . BOO ,01461 .00358 .461 
-.00294 -.00291 -.00288 .825 .01449 .01755 ,400 
5000. -.00378 -.00344 - D0321 - .00304 -.00290 -.00279 -.00276 - .00274 
-.00271 -.00269 -.00266 CL CDI 
10000. -.00345 -.00313 D0292 - .00277 -.00265 -.00254 -.00252 - .00249 
-.00247 -.00245 -.00243 .050 .00011 
iSm-.HS C17-MIDDLE-FLOPS-OUT 100 .00044 320DDO. 28000 30496. 21P54. 14662. .too; .7500 445 i . 0104 
350 .00099 4 1 1112.3 .1104 15,20 >- .0 .00 
200 .00377 -> 4000 28000 30496. 4 449. 14956. .6908 .7500 445 9 . 0293 
250 00276 4 1 1138 .3 .32S9 15 52 4 . 0 . OU 
300 .00398 352000. 28000 30496. 22270. 15266 . . 6855 .7500 445 9 .0292 
.35 .00542 4 1 10SS.2 .3415 15 81 4 -0 . DO 
4 00 .00707 3S9000. 08000 30496. 22914. 15S93. .6005 .7500 445 0 . C0S5 
450 .00895 4 9 930.3 . 3_- • _c 06 4 . 0 .00 
500 .01105 384U0D. 26000, j 096. 23581. 15932. . 6756 ,7500 445 9 .0079 
330 ,01337 + 9 313.2 .372 5 . 6 23 4 . 4 . 00 
600 .D1592 4000DO. 26000 30496. 242.70. 16284 . , 6709 .7500 440 0- .0273 
65D .01663 4 S 
702 . 8 .3880 16 48 4 0 ,00 700 .02166 11 f OC 28000 
3 . 16 . 24998. 16661. . 0665 . 7500 445 9 .02 67 750 .1 .14- "/ 4 6 596 8 .4035 16 64 4 0 . 00 4 3 2 " C 0 . 2SO0O 3U496. 25820. 17087, . 6618 .7500 445 9 .0260 
PRESSURE DRAG COEFFICIENTS.. OOP + 9 
483 .7 .4191 0 6 73 4 .0 .00 MACH CL 448000, 280U0 
3 0496 . 
26703, 17552. . 657 3 .7500 445 9 . 0254 
.05D . ] I fi .150 . 200 .250 .300 .0 00 , 400 .450 4 0 
382. 3 .4346 1 6 73 4 0 .00 + . 500 . 600 . 650 . 7U0 .750 464000. 2BD00 30496, 27646. 18053. .6500 . 7500 4 40 .0247 . 200 .00065 . 00034 .00021 .00028 .O0U53 ,00087 0013 0 .00168 00267 4 0 277.3 .•104 1 7d 4 0 , CO) •..'•Oil . 
00588 009 16 01069 01454 01965 18U0U0. 290)00 30496. 28674. 13599. . 6487 .7500 445 9 . 00 39 
. 300 . coots .00034 .00021 . 0 0. ! •0DQ53 . 00007 0013D 00168 U02C7 . 4 7 171 .4 . 4 656 16 74 4 ('J . 00 
* 00404 00534 00316 01069 . n 1 4 o 0 01965 496000. 2 0 -;<} 30805. 29708. 19203. . 6464 .7500 446 3 . 0232 
.400 .00055 -Q0D34 .00021 . 00023 . 10053 .00087 00130 00169 00267 4 4 100.0 .4" 4 16 7 0 4 0 .00 
+• O04O4 . 00583 ooaifi 01069 . "1454 . 01965 512000. 27100 ,7 . 30627. 19E57. . 6483 .7500 447 6 .0.145 
. boo .00065 .00034 .00021 700 2 8 .00053 .00037 00131 .00171 002 68 4 4 loo. o .4772 16 72 4 0 , 00 • 00404 OC53B 00816 01069 01454 01965 928000. 26423 J2704. 31542. 20507. . 6502 . 750C 443 8 .0216 .600 .i 04 ( ,4,3, .00021 .UUU28 .0UU52 .oooes 90X51 00175 00270 * 9 100.0 .4776 !•" 74 4 0 . 00 
005BB 00316 01069 01454 0196! 544000. 25751 30045. 32452. 21154, . 6519 .7500 450 1 . 0212 
.700 .00076 .00037 . 00022 .00030 .00061 .00099 0014S or xi 00273 8 i oo. o . 4178 6 76 4 0 K 
+ 001D4 00589 00316 01O6B 01403 01961 56QQD0. 25082 34581. 33356. 21798. . 6535 7500 451 4 , 0207 
. J2S .00080 . Q0038 .00021 .00030 .00' . .00104 00150 00195 00275 . + 1 100.0 .4777 16 79 4 0 .00 
+ 00407 00592 00316 01064 . 
014*7 
UI 957 576000, 24497 35540. 34283. 22472. . 6555 , 7500 452 5 . OO. ('1 
.7S0 .00092 .0004 1 00O21 .00032 ,00073 .0D116 00162 00.1 9 00295 . 4 3 100.0 .4790 16 80 4 0 .oo 
+• 0043Q . 00869 01097 01456 . 01938 592000. 23925 36499. 3
 5210. 
20i4 0. . 6574 . 7SO0 453 - ,0195 .7"5 
.00 • .00043 .0DO22 .00036 .00091 .00141 00189 00249 00398 4 9 100 . 0 .4303 16 81 4 0 .00 
f 00605 00355 01108 011.63 01639 . 02079 609000. 233 55 37453. 36133. 23822. .6593 . 7500 454 .0190 
.Si."1 .00151 . i. 062 .00029 .00050 . 00127 00201 30267 0O40C 00532 + 8 1D0.O 3 16 33 4 0 . 00 
+ 00373 . 01175 0L193 017 03 OO.i.07 . 02441 (124000. 22788 3*404. 37052. .. 190. .6410 . 7500 455 6 .0186 
-B25 .00232 . 00106 .00033 .n: .00202 . 00387 00622 00947 0X2 4 5 . 4 0 10D.0 .4821 16 . 84 4 rC .00 
+ 015 92 0 0 <, r. , 02321 02 6 03 02997 03319 6400DO. 22224 39350. 37967. 25160. . 6t-.2 7 .7S00 456 7 .0181 
+ 5 100.0 . 4B27 16 . fi0 4 0 .00 
656000, 216 62 •.-•193. 38877. 25825. . 6643 .7500 457 7 ,0173 
» CRUISE OPTIMIZATION RESULTS 4 2 100.0 . 4831 16 87 4 0 .00 
672000. 21102 41230. 39784. 26487. . 6658 . 7500 458 7 .0173 4 
2 100.0 .480 3 0 ' S9 4 0 . 00 
DATA FX R CRUISE SCHEDUI 
E 1 
WEIGHT ALTITUDE THRUST FUEL SFC MACH VELOCI . V SPFjCTF! r 01UISE SCH 
4nui F. RANGE AND Tj Ml 
I SUMMARY 
C RATE OF
 Cl 
L/D EK3I HES
 NOX 
AVAlLAO[,E REQUIRED FLOW NUMBER RANGE WEIGH! RANGE -1 - I
 I ME 
CLIMB 
•.!• TING PATE (POliNLJr: j (N.K. ) (RR) 672000. 0 .00 208000. 30496- 17565 . 12956. . 7376 
.'.'00! II 
445 . 9 .0344 . 139 4 .30 
1 2307 .1 .20;|3 11. 34 4 . 0 . 00 656OO0. 280 3 .61 
221000. 28000. 10496. 17962. 13149. . 7321 . 7500 4
 0 
. 9 . 0339 648OO0. 420 0 . 92 4 
1 2526.5 .2173 12 
47 4 . e .00 640000. 567 3 1.24 240000, 24000, 00405. 18412. 13368. .7250 .7500 445 . 9 .0333 •:>: 713 4 I. it 5 2273 <! .232:3 15. 03 t . U . 00 624000. 01 3 
l .hi 256000. 23000. 30496. 1(5914 . 13 613. .7197 .7 500 445 .9 . 0327 616000. 1 0 1 i 1 2.21 + 5 2042 ,B .2433 1- . S3 4 ,0 .00 608000. 1162 7 2 55 
272000. 29000. 30496. 19416. 13857 , .7137 .7500 44" .0321 6OOOOO. 0316 4 2 . 8B 8
 ] 339 
.3 .2639 04. 01 4 .00 592000. 1472 1 3.23 
2380O0. 23000. 30496. 19938, 14111. .7078 .7500 5 . 9 , 0306 584000. 1629 9 3 • 58 
+ 0 1655 .3 .2794 14. 44 4 .0 . 00 07 04.10. :•>: 4 3.91 
3040.00, 0SU0D. 1D49F• .: 100. 143B0. . 7021 . 0' •] [00 445 . 9 .0310 568000. 1952 1 4.20 
1 14B7 .2 .29 
Ii ;l _ 4 . 
B4 4 .0 .00 fj 60000. 2116 E 4 . 65 
15:09:05 C17-MIDDLE-FLOPS-OUT 
START HOLDING CLIMB CLIMB CRUISE 
RESERVE END 
RESERVE FUEL DIST FUEL DIST 
FUEL RESERVE MACH 
WEIGHT 
WEIGHT NUMBER ALTITUDE VELOCITY 
208000. 0. 29.3 2708,9 376.0 
17049. 190951. .7500 28000. 445.9 
224000. 0. 32.1 2950.7 372.6 
17238. 206762. ,7500 28000. 445.9 
240000. 0. 35.0 3199.0 369.1 
17575, 222425. .7500 28000. 445.9 
256000. 0. 38.0 3455.3 365.6 
17933. 238067. .7500 28000. 445.9 
272000. 0. 41.0 3720.2 361.8 
18306. 253694. .7500 28000. 445.9 
CRUISE 
FUEL 
10967.2 
10890.7 
10954.7 
11033.1 
11111.6 
DESCENT DESCENT 
DIST FUEL 
94 .7 
95.3 
95, S 
96 .4 
97 . 1 
1506.5 
1531.0 
1555.2 
1578.5 
1607.8 
* ITERATION 1 
* ITERATION 2 
* ITERATION 3 
* ITERATION 4 
* ITERATION 5 
* ITERATION 6 
RANGE = 
RANGE = 
RANGE = 
RANGE = 
RANGE = 
RANGE = 
7237.757 
4211.770 
3856.730 
3900.612 
3900,007 
3900.000 
(t OUTPUT FROM THE WEIGHTS MODULE 
DESCRIPTION 
FOR GROSS WEIGHT = 
FOR GROSS WEIGHT = 
FOR GROSS WEIGHT = 
FOR GROSS WEIGHT = 
FOR GROSS WEIGHT . 
FOR GROSS WEIGHT = 
VALUE DIMENSIONS 
650000 
505364 
490462 
492278 
4922 53 
492252 
00 
20 
27 
41 
10 
79 
552000 2283 3 5 02 288000. 0. 44 2 3993 7 358 0 11187 5 97 8 1634 6 
544000 2452 4 5 40 + 18682. 269318 .7500 28000. 445 9 
536000 2623 8 5 78 304000. 0 . 47 4 4277 6 354 3 11269 9 98 3 1656 3 
528000 2797 7 6 17 4 19070. 284930 .7500 28000. 445 9 
520000 2974 0 6 56 320000. 0. 50 7 4570 8 350 6 11359 3 98 7 1673 9 
512000 3153 0 6 96 + 19470. 300530 .7500 28OO0. 445 9 
504000 3334 7 7 36 336000. 0, 54 2 4875 9 346 8 11450 8 99 0 1688 2 
496000 3519 2 7 78 + 19881. 316119 .7500 28000. 445 9 
488000 3706 6 8 20 352000. 0 . 57 9 5194 9 342 9 11543 0 99 2 1700 9 
480000 3896 9 8 62 + 20305. 331695 .7500 23000. 445 9 
472000 4090 1 9 06 368000. 0. 61 8 5527 6 338 8 11636 6 99 4 1711 8 
464000 4286 2 9 50 + 20742. 347258 .7500 28OO0. 445 9 
456000 4435 1 9 94 384000. 0 , 65 8 5876 7 334 6 11730 3 99 6 1721 2 
448000 4686 9 10 40 4 21194. 362806 .7500 28000. 445 9 
440000 4891 5 10 85 400000, o. 70 1 6243 0 330 2 11821 9 99 6 1728 6 
432OO0 5098 9 11 32 + 21660. 378340 .7500 28000. 445 9 
424000 5308 9 11 79 416000. 0. 74 8 6630 7 325 6 11909 6 99 6 1735 3 
416000 5521 7 12 27 + 22142. 393358 ,7500 28000. 445 9 
408000 5737 0 12 75 432000. o. 79 8 7044 0 320 5 11994 6 99 6 1741 6 
400000 5954 8 13 24 + 22646. 409354 .7500 28000, 445 9 
392000 6175 0 13 73 448000. 0, 85 4 7487 4 315 0 12083 0 99 6 1747 6 
38400C 6397 7 14 23 + 23184. 424816 .7500 28000. 445 9 
376000 6622 8 14 74 464000, 0. 91 6 7971 0 308 S 12160 5 99 6 1753 6 
368000 6850 3 15 25 4 23751. 440249 .7500 28000. 445 9 
360000 7080 3 15 76 480000. o. 93 7 8505 0 301 9 12217 7 99 5 17S8 7 
352000 7312 7 16 29 + 24348. 455652 .7500 28000. 445 9 
344000 7547 5 16 81 496000. 0. 105 8 9054 1 294 9 12287 5 99 4 1763 2 
336000 7784 8 17 34 4 24971. 471029 .7500 27779. 446 3 
328000 8024 5 17 88 512000. 0, 109 9 9471 4 291 1 12502 3 98 9 1764 9 
320000 8266 6 18 42 4 25605. 486395 .7500 27100. 447 6 
312000 8511 0 18 97 528000, o. 110 5 9714 0 291 7 12901 8 97 8 1759 5 
304000 8757 9 19 S3 4 26241. 501759 .7500 26423. 448 a 
296000 9007 1 20 09 544000, 0. 110 4 9922 4 293 6 13359 0 96 0 1748 2 
288000 9258 7 20 65 4 26896, 517104 .7500 25751. 450 1 
280000 9512 6 21 22 560000. 0. 110 3 10130 6 295 5 13818 5 94 2 1736 S 
272000 9768 8 21 79 4 27552 . 532448 .7500 25082, 451 4 
264000 10027 4 22 37 576000. o. 110 3 10351 6 297 2 14274 3 92 5 1723 9 
256000 10288 2 22 96 4 28216. 547784 .7500 24497. 452 5 
248000 10551 5 23 55 592000. 0. 110 8 10604 2 298 5 14724 9 90 a 1710 8 
240000 10817 1 24 14 4 28906. 563094 .7500 23925. 453 5 
232000 11085 0 24 75 608000. 0 . 111 5 10879 7 299 3 15161 8 89 2 1700 6 
224000 11355 1 25 35 4 29608. 578392 .7500 23355. 454 6 
216000 11627 4 25 96 624000. 0. 112 2 11164 6 300 1 15600 9 87 7 1689 4 
203000 11901 7 26 58 4 30321. 593679 .7500 22788. 455 6 
640000. 0. 112 8 11461 2 301 0 16042 1 86 2 1677 9 
4 31047. 608953 .7500 22224, 456 7 
RESERVE SUMMARY 
4 
656000, 
31797. 624203 
o. 113 
.7500 
5 11789 
21662. 
0 
457 
301 
7 
7 16475 2 84 7 1666 3 
4ISSED APPROACH FUEL = 1866. LB. 672000. 0. 114 4 12163 2 302 4 16900 0 83 2 1653 3 
4 32583. 639417 .7500 21102. 458 7 
Nov 18 96 
15:09:05 C17-MIDDLE-FLOPS-OUT 
CALCULATED WING AREA 
CALCULATED ASPECT RATIO 
WING BENDING FACTOR 
ENGINE INERTIA RELIEF FACTOR 
WING WEIGHT BREAKDOWN 
TERM 1 
TERM 2 
TERM 3 
WING SPAN 
WING GLOVE AREA 
HORIZONTAL TAIL AREA 
MODIFIED VOLUME COEFFICIENT 
VERTICAL TAIL AREA 
MODIFIED VOLUME COEFFICIENT 
NACELLE LENGTH 
NACELLE DIAMETER 
LENGTH OF MAIN GEAR 
LENGTH OF NOSE GEAR 
MAXIMUM LANDING WEIGHT 
WING FUEL CAPACITY 
FUSELAGE FUEL CAPACITY 
AUXILIARY TANK CAPACITY 
TOTAL FUEL CAPACITY 
1 MASS AND BALANCE SUMMARY 
T LREF HORI CG-INCHES 
WING 
.0 .0 
HORIZONTAL TAIL 
.0 .0 
VERTICAL TAIL 
.0 .0 
VERTICAL FIN 
.0 .0 
FUSELAGE 
,0 .0 
LANDING GEAR 
.0 .0 
NACELLE (AIR INDUCTION) 
.0 .0 
STRUCTURE TOTAL 
0) ( .0) 
ENGINES 
.0 .0 
THRUST REVERSERS 
,0 73.4 
MISCELLANEOUS SYSTEMS 
.0 .0 
FUEL SYSTEM-TANKS AND PLUMBING 
.0 .0 
PROPULSION TOTAL 
,0) [ .0) 
SURFACE CONTROLS 
.0 .0 
AUXILIARY POWER 
.0 .0 
INSTRUMENTS 
.0 .0 
3846.0 SQ FT 
7 . 28618 
3.2021 
.926587 
14181.7 LB 
19559.7 LB 
7829.7 LB 
167.40 FT 
-92.05 SQ FT 
845 . 00 SQ FT 
1.539989 
395.07 SQ FT 
.100000 
12.23 FT 
6.23 FT 
41.91 IN 
29.33 IN 
348268.8 LB 
182720.0 LB 
.0 LB 
,0 LB 
182720.0 LE 
PERCENT WREF 
8 .45 
.63 
.27 
.21 
13.04 
2 .40 
.71 
[ 25.69) 
5 .77 
.00 
.19 
.40 
! 6.37) 
.93 
.13 
. 19 
POUNDS 
41571. 
3080. 
1315 . 
1028 . 
64181. 
11790. 
3478 . 
( 126443.) 
28400. 
0. 
959. 
1984 . 
( 31343.) 
4563 . 
616 , 
913 . 
HYDRAULICS 
.0 .0 
ELECTRICAL 
.0 .0 
AVIONICS 
.0 ,0 
FURNISHINGS AND EQUIPMENT 
.0 .0 
AIR CONDITIONING 
,0 .0 
ANTI-ICING 
.0 .0 
SYSTEMS AND EQUIPMENT TOTAL 
.0) ( .0) 
WEIGHT EMPTY 
.0 
.0 
.0 
.0 
. 0 
.0 
CREW AND BAGGAGE-FLIGHT, 3 
,0 
-CABIN, 0 
.0 
UNUSABLE FUEL 
.0 
ENGINE OIL 
.0 
PASSENGER SERVICE 
.0 
CARGO CONTAINERS 
.0 
OPERATING WEIGHT 
,0 
PASSENGERS, 0 
.0 
PASSENGER BAGGAGE 
CARGO 
.0 
ZERO FUEL WEIGHT 
.0 .0 
MISSION FUEL 
.0 
RAMP (GROSS) WEIGHT 
,0 .0 
I NONCRUISE SEGMENT RESULTS 
CLIMB PROFILE DATA FOR SEGMENT 1 
+. - - - CUMULATIVE - - -
WEIGHT ENERGY ALT MACH 
+ TIME DIST FUEL CL L/D 
,52 
. 64 
. 52 
2.87 
.46 
.06 
( 6.30) 
38.36 
.14 
,00 
. 20 
. 07 
.00 
4.19 
42.96 
.00 
. 00 
22.75 
65 .71 
34 .29 
100.00 
2541 . 
3155 , 
2556. 
14129. 
2244 . 
311. 
( 31029.) 
188816. 
675 . 
0. 
983 , 
325 . 
0. 
20650. 
211450. 
0. 
0. 
112000. 
323450. 
VEL RCI PC TIME DIST 
THRUST /TMAX 
INCREMENTAL- -
FUEL 
489267. 1743. 0. .300 198.4 2602. 1 .00 ,0 .0 133.3 
.00 .0 .0 .966 8.68 119703. 1.000 
488828. 3403. 0. .419 277.3 4581. 1 .46 1.8 439.5 260.2 
.46 1.8 439.5 .494 17.68 107400. 1.000 
488494. 5063. 0. .511 338.2 4989. 1 .35 1.8 333.6 387.2 
.81 3.6 773.1 .332 17.60 98916. 1.000 
488172. 6722. 1107. .540 356.2 4893. 1 .34 1.9 321.6 415.7 
Nov lit 96 
15:09:05 C17-MTDDLE-FLOPS-OUT 
i n 5 
1B7B51. 
1.45 7 
4B7529. 
i . 8 i 3 
437506. 
^ . 2 1 !.,! 
486801. 
2.5B 14 
. -. • >3. 
2.95 17 
4B6213 . 3-41
 33 
486670. 
3.35 23 
4B5S19. 
4.32 26 
4 85157. 
4.83 3 3 
484781. 
5.38 34 
454385. 
5.93 3 8 
483977. 
6.63 43 
45354:'. 
7.46 49 
483069. 
B.36 56, 
483537. 9.13
 64. 
161334. 
L0.70 73. 
4111314. 
72.32 I 
480479. 
14.48 131 
480356. 
14.3. 104. 
5 1094 
8332 . 
6 1416 
-.•"•042 . 7 ] 73; 11701. 
11361 
23 = 3 3 4048 2 
5085 7 6522 
23 66.2 15020. 
1 2717 
16680. 
5 3054 
183 40, 
7994 5 
9107 
I 1D2B6 
3 
1759 
0 339 19999. 
3 374 .1 21659 13153 0 1110.3 23319. 14513 
14 66,4 
24978. 1CT17J 
S 1878.7 
26638. 17B11 
7 5295.3 
28296. 19191 
5 5727 5 1 :I957 . 21153 
2 6197.6 
31617.. 223.1 5 
1 6709.9 
33277. 24473 
6 7261.5 
34936. 26134 
6 7953.4 
36596. 27794 
7 87H8.5 
36797. 27995 
1 8908.7 
.309 .313 
.3.6 .295 
.35? .10] 
.301 .2 84 
.290 . 394 
.336 
312 .330 
. 348 .368 
.390 .412 
. 437 . 4 63 
.466 
17 ,15 
552 
17,17 3
 6-', 
17 . 17 
595 
16. 64 
6 54 
16, 75 
620 15.53 
E3.il 
10.31 
669 
15 . 91 
680 
16 .00 
695 
15. 97 
711 
15 . 83 
715 
16.15 
720 
13.39 
724 
16 , 60 
723 
16 . 77 
734 
16 . 92 
739 
16.99 
744 
16.94 749 
16 .77 
750 
16.74 
94633 361,7 51510 367 ,9 
33692 336.6 
• m 390.2 BI119 
398 .4 
77420 1DB.1 /413 6 42 5 . 5 
72101 431
 .4 63291. 439 .3 
64701 
446.0 
61361 
44o.5 
57536 
446.0 53B76 416,0 50203. 
445 .0 
46939. 
445 .9 
43851. 
445 . 9 40751. 
445 . 9 37599. 415.9 
35402 . 
445 .9 7
 5 588. 
1.000 
4741 . 
1 .000 
160 8 . I
 . 330 
4556. 
1. OOO 
4249, 
1.006 
3998. 1.000 
3798. 
1.000 
3700, 
1 . 000 
3415. 
1 .000 
3140. 
1 ,000 
2373. 1
 . OOU 
5568. l.ODO 2772 . 
1 .000 
3 968. I.OOO 
1696. 
1 .000 
1434, 
1 .000 1160. 
1.000 319 . 
1 .ODO 
65 7 . 
1.000 
651 . 
1 .050 DESCENT PROFILE 3JATA FOR SEGMENT • - - CUHULA7 1VT-: - - -
•.(EIGHT ENT13.GY AJ.T TIMS DIST FUEL MACH 
2.7 37 89 . 223 735. 3743 . 0. 
VEL 3.CI THP.tVi /THA* 
198.4 -1147. 
. 34 
.36 
2.0 
2 .1 .36 2,3 .33 2.4 
.40 2 . 6 .43 2.9 
.44 3.1 
,47 
55 
3 .3 
4 . 1 ,61 4.5 
.69 5.7 .78 5.8 
.91 7.53 6 .7 
7 , 9 1.28 9.5 1,61 12.0 
2.16 16.1 .32
 2.4 
121 .7 322 .0 
322 .5 
336.9 3 42 ,8 
353. 9 362 .2 
376.1 392
 a 417 .7 
437 .2 470 .1 
713.7 573 . 6 
655 . 7 835.2 
120.1 
- - INCREMENTAL-PC TIME DIST 33 
.00 . 5 .452 17,33 .000 3403 . 1623 , .35-200.5 1 •; 0 -1.44 -1.44 4,a -346.0 .464 17.42 229072. 5063. 3255. ,113 -2.8'
- 9.5 - 572.8 .467 17,39 229230. 6725 4785. .322 
-4.22 14.3 -411.0 .469 17.36 229330. 5782. 5755. .337 •3.56 .!.:,-. 0 -531 .3 ,471 17.21 
0. .05 3 204.8 -1193. 0 -1.41 0. .050 209.3 -1223. 0 -1.38 
0. .000 214.0 -1250. 3 -1.34 0. .050 
.340 .473 17.30 229431. 10!'42. "1923. 
-6.87 23.7 -642,1 
52533b. 11701. 51 SC. -8,1S 2K.4 -745 3' .475 77.27 
29630. 13361. 11044. .360 223.3 
-9.|: 33.1 -341.45 .477 17..74 
259719, 1^573 12j:'-1. .2 70 233.3 
13.62 37.3 -929.S .480 '.20 
229799. 16630. 14146. -381 233.2 
11.81 43.5 - -'1 0.6 .482 j.Z.16 
218.8 -2281 -1.31 . 000 .350 223.7 -1312, 0 -1.28 0 . ,OOO -1344. 3 -1.25 0. .030 
-1377. 0 -1.22 5. 030 1412. 3 -1.19 5. .000 
4 . 7 4 .7 
4 .7 4.7 
4 .7 1 .7 
4 . 7 4 .7 
-146 -136 
-128 -119 
-311 -103 
-95 
110,4 5 5 5.5 
434 . 9 422 , 7 
422 . 5 42 5. 6 
450.8 440.3 
134 .7 430 .7 
386 .1 365 .2 
315.2 326.0 
307.6 290.1 
273 . 3 271 .3 
133 .3 129.7 
129.2 128 . 6 
128 .2 127,7 
137.2 
li6 . 6 125.0 
125.4 
229B73. 18340. 14690. .392 244 
12,97 47.2 -1031,2 .185 17.15 
229939. 19*99. 17256. ;«1 25b 
14.11 51,8 -1150.6 .193 17.32 
229999. 21659 1NH75. .4'l" 755 15.5654
 -1339.3 .513 16.78 
230051. 23319. 20444, ,416 254 
16.30 61.0 -1152.2 .524 16,63 
J3O098. 21973. 22013. .425 253 
17.35 65.5 -1303.a .536 36.45 
23QI33. 26618. 23591, .433 262 
18.38 70,0 -1549.S .551 16.2^ 
220175. 282.tli. 25175, ,441 265 
19.3B 74.3 -1335.7 .569 IS.95 
210205. 39957. 26762. .450 2I* 
30.35 78.6 -1116.6 .588 i 5.63 
230235, 31317 28000. ,481 285 
21.29 83.0 -1446.3 .543 16.31 
230273. 33277. 23000. .53! 345. 
22.16 87. U -7 483.8 .373 lrj.52 
230313. 34936. 28000. .666 395. 
22,66 91.9 5524.2 .233 15.07 
230350. 36596. 28000. .741 440 
2:3.40 95.7 -1560.8 .22^ 5.58 
230351. 36801. 2SOO0. ,7 50 445. 
23.46 55.1 -1555.0 .223 12,70 
6 -1147, 0 -1.1* 
0. .000 5 •1431. 0-1.13 D.
 .000 8 -J 514. 0-1.11 3. .000 :• -1552 . 0 -"i . M 
0. .OOO 8 -1593. 0 -1.06 0. .OOO 4 -163:7. 0 -1.03 
0. .UUU 
F: -165 6 . 0 -1 .00 5. .500 3 7/13. 0 -.97 0. .000 
8 -1774. 0 -.94 0- .000 2 -2067. 0 .35 3.
 .000 B 2361. 0 -.70 
0. -000 6 -3437. 0 -.51 0 . . 3 U Ll 9 -3555. 0 -.0' 
0. .000 
5ERATI0N 7 -- RANGE 3 900.000 FOR GROSS WEIGHT = # SIZING AND PERFORMANCE RLSilLTS 
CONFIGURATION DATA AFTER RESIZING (IF OPSRATINij WEIGHT EMPTY 215449.6 PAYLOAD UJ 000.0 
MAXIMUM FUEL 16B803.2 gross weight 19j.252 .8 
hefescemce wing area 3800.00 wing loading 129.51 thrust per engine 40700.7 ehoine scale factor 1.0350 
T&lF.USk-W77IGHT RAI , O .335 7 
L3 LH LB LB 
SQ FT LB/SQ FT 
4.7 4 .7 
4 . 6 4.6 
4 . 5 4 . 5 
4 .4 4.3 
4 .4 
-73 .6 -66 .4 
- 7 q 2 -52 . 4 
-46.3 -4. : 
-35.8 -30. 9 
-30.0 -37
 .2 -40 .4 
-3 6.5 -4
 .2 
52.79 
112 .9 159.6 
105.5 103 . 0 
111. 5 162 . 6 
213 .8 2 65.0 
271 .3 
• H NUMHRFl SEGMENT * T END 
5 a:-TAKE OFF + .309 
INITIAL FUEL(LB) ALTITUDE (FT) NOX LMLSSU - I WEI-3HT(LB) SEGMT TOTAL SEGMT START END SEGMT TOTAL MISSION SUMMARY **« TIME(MIN) DISTANCE(N MI) TOTAL
 SSgjfT TTOTHL 192253. 
43;133. 1120 . 1366 . 0. CLIMB
 489267. 8939. ' 0 .750 0, 27995. CRUISE 480356. 123938, + 0 .750 27995. .7 5353 
RELEASE 356421. 0. i- 5 .730 28000. 23000, REFUEL 244421: 2000. , 3 .755 23300. 23000. 
CRUISE 242421. 12067. 
1120. 
2533 . 11894 . ,00 13~532. , 00 135832. .00 
137832. 
,00 119899 . 
.01 .50 
15.0 2
 . 0 
' . 3 .5 
. 0 -. 5 
54 .3 
15.0 17. 0 
31 . 8 
475.3 
475 .3 
533. 3 634
 .7 
104 . 1 3 2 5 5 .
 3 . 0 
. 0 4 3.1 ,9 
104. 1 3400.0 
3433.0 3 4GC.O 
3803.9 
MAC STAR 
.30 . 75 
.75 .75 
.75 
Nov 18 96 
15:09:05 C17-MIDDLE-FLOPS-OUT 
0 .750 23000. 28000. .00 .00 
DESCENT 230354. 1565. 151464, 23.5 
0 .300 28000. 0. .00 .00 
RESERVES 
TAXI IN 
ZERO FUEL 
228789. 
211450. 
17339. 
149 , 
168803 . 
2.0 
658.1 96.1 3900.0 
660.1 
DESIGN RANGE 
FLIGHT TIME 
3900.0 
641 . 1 
BLOCK TIME = 11.00 HOURS 
BLOCK FUEL = 151613.3 POUNDS 
TOTAL NITROGEN OXIDES EMISSIONS 
ATA TRAFFIC ALLOWANCE -
AIR MANEUVER = 44,6 
AIRPORT TRAFFIC ALLOWANCE = 17.4 
AIRWAY DISTANCE FACTOR = 78.0 
0. POUNDS 
140.0 NAUTICAL MILES 
ATA RANGE 3900.0 NAUTICAL MILES 
H DETAILED FLIGHT SEGMENT SUMMARY 
WEIGHT 
CLIFT 
489267. 
.96574 
,11123 
488828. 
.49431 
. 02796 
488494, 
.33203 
488172. 
.30903 
. 01802 
487851. 
.31283 
437529. 
.31564 
.01838 
487206, 
.29484 
.01772 
486881, 
1 CLIMB 
ALTITUDE 
LIFT 
ENERGY 
MACH NO. DELTA T 
L/D Q 
VELOCITY TIME 
DRAG SP RANGE 
0. 
489267. 
1743 . 
56353. 
488828. 
3403 . 
27643. 
0 . 
488494. 
5063. 
27756. 
1107 . 
488172. 
6722 . 
28461. 
2589 . 
487351. 
8382 . 
28406. 
4048. 
487529. 
10042. 
28395. 
5085 , 
487206, 
11701. 
29282. 
6622 . 
. 3000 
8.682 
198 . 44 
.00350 
.4191 
17.680 
277.25 
.00483 
.5112 
17.600 
338.17 
.00583 
.5405 
17.152 
356.16 
.00626 
.5518 
17.174 
361.73 
.00656 
.5641 
17.169 
367.94 
.00686 
. 5949 
16.638 
386 .58 
.00727 
. 6037 
NOX 
.00 
133 . 3 
17 . 00 
.0 
. 46 
260.2 
17.46 
.0 
.35 
387.2 
17.81 
. 0 
.34 
415.7 
18.14 
. 0 
.34 
410. 4 
18.49 
.0 
.36 
406 . 5 
18.84 
.0 
.36 
434 . 9 
19.21 
DELTA D 
PCODE 
DIST 
ENG PAR 
.0 
1 
.0 
. 000 
1.8 
1 
1.8 
,000 
1.8 
1 
3 . 6 
.000 
1.9 
1 
5.5 
.000 
2.0 
1 
7 . 6 
. 000 
2.1 
1 
9.7 
.000 
2.3 
1 
12 .C 
.000 
2.4 
DELTA F 
FUEL 
0. 
2986 , 
439. 
3425. 
334. 
3759 . 
322 . 
4080. 
322. 
4402 . 
322 . 
4724. 
322. 
504 6. 
326. 
THRUST FUEL FLOW EX POW 
T/TMAX SFC DH/DT* 
119703, 56725. 2602.1 
1.00000 .47388 .0 
107400. 57392. 4580.7 
1.00000 .53438 .0 
98916. 58017. 4988.7 
1.00000 .58653 .0 
94683. 56855. 4892,6 
1.00000 .60047 3294.7 
91540. 55167. 4740.6 
1.00000 .60265 4302.6 
88692. 53653. 4608.3 
1.00000 .60494 4109.1 
S5976. 53176. 4555.6 
1.00000 .61850 2863.1 
81419. 50442. 4248.8 
. 30314 
.01809 
486550. 
.30304 
.01819 
486213. 
.30062 
. 01821 
485870, 
.28361 
.01779 
485519. 
.29020 
.01814 
486881 . 
13361. 
29062. 
7994 . 
486550. 
15020. 
29201. 
9307 . 
486213. 
16680. 
29458. 
10286. 
485870. 
18340. 
30482. 
11759. 
485519. 
19999. 
30343, 
485157. 13153. 
.29373 485157. 
21659. 
30387. .01840 
484781. 14513, 
.29622 484781. 
23319 . 
30521. .01865 
4843 88. 
.31249 
.01935 
483977. 
.32986 
.02013 
16173. 
484388. 
24978, 
29993. 
17833. 
483977. 
26638. 
29532. 
483540. 19493. 
.34843 483540. 
28298. 
29137. . 0210C 
483069 
.36829 
. 02196 
432557. 
.38954 
.02303 
481984. 
.41229 
. 02427 
481314. 
.43662 
21153. 
483069. 
29957. 
28801. 
22813. 
482557. 
31617. 
28524. 
24473. 
481984. 
33277, 
28374. 
26134. 
481314. 
34936. 
16.753 
390.15 
.00773 
. 6196 
16.662 
398.41 
.00825 
.6377 
16 . 505 
408.11 
.00875 
. 6689 
15.939 
426.52 
.00922 
. 6803 
16.001 
431.44 
.00981 
. 6948 
15.966 
438.33 
.01047 
.7106 
15.883 
446.00 
.01118 
.7151 
16.150 
445.99 
.01197 
.7197 
16.388 
445.98 
.01283 
.7244 
16 .595 
445.97 
.01383 
.7292 
16.773 
445.96 
.01485 
.7341 
16.917 
445.94 
.01596 
.7391 
16.987 
445.93 
.01725 
.7442 
16.938 
445.91 
422 .7 
19.58 
.40 
422 .5 
19 .99 
.43 
425 .6 
20.41 
.0 
.44 
450.8 
20.85 
,0 
,47 
440.3 
21 .32 
.0 
.51 
434.7 
21 .83 
.0 
.55 
430.7 
22.3a 
.0 
,61 
407 .9 
22.99 
.0 
.69 
336.1 
23 .6S 
.0 
.78 
365 .2 
24 .46 
.0 
.91 
345,2 
25 .36 
1 .06 
326.0 
26.43 
.0 
1 
307 
28 
6 
27.70 
, 0 
1 
290 
61 
1 
29 . 32 
1 
14 . 4 
. 000 
2.6 
1 
17.1 
.000 
2 . 9 
1 
19.9 
.000 
3.1 
1 
23 .0 
.000 
3.3 
1 
26 .3 
.000 
3.7 
1 
30 .0 
,000 
4.1 
1 
34.1 
.000 
4.5 
1 
38 . 6 
.000 
5.1 
1 
43 .7 
, 000 
5. 8 
1 
49.5 
.000 
6.7 
1 
56 .2 
. 000 
7.9 
1 
64 .1 
.000 
9.5 
1 
73 . 6 
,000 
12 . 0 
1 
85.6 
5372 . 1.00000 .61953 4076.5 
331. 77420. 48314. 3998.5 
5703. 1.00000 .62405 3407.4 
337. 74136. 46649. 3797.7 
6040, 1.00000 .62924 3034.4 
343. 72101. 46275. 3699.9 
6383. 1.00000 .64181 2212.2 
351. 68291. 43968. 3414.9 
6734. 1.00000 .64383 3157.3 
362. 64701. 41866. 3139.6 
7096. 1.00000 .64707 2752.9 
376. 61361. 39897. 2873,2 
7472. 1.00000 .65020 2462.8 
392. 57536. 37266. 2568.1 
7864. 1.00000 .64771 2721.3 
412. 53876. 34763. 2271.8 
8276. 1.00000 .64525 2420.5 
437. 50203. 32235. 1967.5 
8713. 1.00000 .64210 2120.2 
470. 46939. 30026. 1695.8 
9183. 1.00000 .63967 1832.2 
512. 43851. 27946. 1434.4 
9696. 1.00000 .63729 1565.6 
574. 40751. 2S845. 1159.6 
10269. 1,00000 .63420 1297.5 
670. 37999. 240O9. 898.9 
10939. 1.00000 .63183 1029.7 
Nov IS 96 
15:09:05 
480479. 
,46262 
.02759 
27794. 
480479. 
36596. 
28653. 
.01857 
.7494 
16.769 
445.89 
.02001 
2.16 
273.3 
31 .48 
.0 
.000 
16.1 
1 
101 .7 
.000 
C17-MIDDLI 
480358. 
.46588 
. 02783 
27995, 
480358. 
36797. 
28696. 
.7500 
16.739 
445.88 
. 02020 
.32 
271 .3 
31.81 
.0 
2.4 
1 
104.1 
.000 
120. 35088. 22078. 600.8 
11394. 1.00000 .62922 618.C 
SEGMENT 2 CRUISE 
WEIGHT 
CLIFT 
ALTITUDE 
LIFT 
ENERGY 
MACH NO. DELTA T 
L/D Q 
VELOCITY TIME 
DRAG SP RANGE 
480358. 27995, 
.46588 480353. 
36797. 
28696. .02783 
480000. 
.46563 
.02782 
464000. 
.45011 
,02682 
2 8000. 
480000. 
36801. 
28674. 
28000. 
464000. 
36801. 
27646. 
.7500 
16,738 
445.88 
.02396 
.7500 
16 .740 
445.88 
.02397 
.7500 
16.783 
445.88 
.02470 
NOX 
.00 
271 .3 
31.81 
1.15 
271. 3 
32.95 
.0 
52.33 
271 .3 
85.34 
.0 
DELTA D 
PCODE 
DIST 
ENG PAR 
.0 
2 
104 . 1 
.000 
8.5 
2 
112 . 6 
. 000 
389 . 3 
2 
501 . 9 
.000 
DELTA F THRUST FUEL FLOW EX POW 
FUEL T/TMAX SFC DH/DT* 
0 . 
11894. 
358. 
12253 , 
28696. 18612. 
.94077 .64860 
28674, 18599, 
.94024 .64865 
169.8 
.0 
171 .4 
4,3 
16000. 27646, 18053. 277.3 
28253. .90655 .65300 .0 
443000. 
.43459 
.02590 
432000. 
.41907 
.02505 
416000. 
.40355 
.02425 
400000. 
.38803 
.02354 
384000. 
,37250 
.02287 
28000. 
448000. 
36801. 
26703. 
28000. 
432000. 
36801. 
25820. 
28000. 
416000. 
36801. 
24998. 
28000. 
400000. 
36B01. 
24270. 
28000. 
384000. 
36801. 
23581. 
. 7500 
16.777 
445 .88 
.02540 
.7500 
16.731 
445.88 
,02609 
,7500 
16.641 
445.88 
.02676 
.750C 
16.481 
445.88 
.02738 
.7500 
16.285 
445.88 
.02799 
53.93 
271.3 
139.27 
, 0 
55 .43 
271.3 
194.70 
.0 
56.90 
271. 3 
251.60 
.0 
58.28 
271 .3 
309.88 
.0 
59.60 
271 .3 
369.48 
. 0 
400.8 
2 
902 .7 
.000 
411 .9 
2 
1314.6 
.000 
422.8 
2 
1737.4 
.000 
433 . 1 
2 
2170.5 
. OOC 
442 . 9 
2 
2613.4 
.000 
16000. 26703. 17552. 
44253. .87563 .65728 
16000. 25820. 17087. 
60253. .84668 .66176 
16000. 
76253. 
16000. 
92253. 
24998, 
.81971 
24270. 
.79585 
16661. 
.66649 
162 84 . 
, 67094 
382.3 
.0 
488.7 
. 0 
596.8 
.0 
702 . 8 
.0 
16000. 23581. 15932. 813.2 
108253. .77324 .67562 .0 
368000. 
.35693 
28000. 
368000. 
36801. 
22914, 
.7500 
16.060 
445.38 
.02859 
60.91 
271.3 
430.39 
,0 
452 . 6 
2 
3066.1 
.000 
16000. 22914. 15593. 930.3 
124253. .75139 .68050 .0 
356421. 
.34575 
28000. 
356421, 
36801. 
.7500 
15.879 
445.88 
44.94 
271.3 
475.33 
333.9 
2 
3400.0 
11579. 22446. 15355. 1019.8 
135832. .73603 .68410 .0 
FLOPS-OUT 
.02177 22446. .02904 .0 
SEGMENT 3 RELEASE 
.000 
WEIGHT ALTITUDE MACH NO. DELTA T 
CLIFT LIFT L/D Q 
ENERGY VELOCITY TIME 
CDRAG DRAG SP RANGE NOX 
244421. 28000. .7500 .00 
,23710 244421. 13.179 271.3 
36801. 445.88 475.33 
.01799 13546. .03319 .0 
DELTA D DELTA F THRUST FUEL FLOW EX POW 
PCODE 
DIST FUEL T/TMAX SFC DH/DT" 
ENG PAR 
3400.0 135832. 
. 000 
18546. 
.60813 
13433 . 
.72433 
2207 .7 
.0 
SEGMENT 4 REFUEL 
WEIGHT ALTITUDE MACH NO. DELTA T 
CLIFT LIFT L/D Q 
ENERGY VELOCITY TIME 
CDRAG DRAG SP RANGE NOX 
242421. 28000. .7500 105.00 
.23516 242421. 13.115 271.3 
36801. 445.88 580.33 
.01793 18485. .03327 .0 
DELTA D DELTA F THRUST FUEL FLOW EX POW 
PCODE 
DIST FUEL T/TMAX SFC DH/DT* 
ENG PAR 
2 000, 
3400,0 137832. 
.000 
18485. 
.60614 
13404, 
.72512 
2237 .2 
.0 
SEGMENT 
WEIGHT 
CLIFT 
CDRAG 
5 CRUISE 
ALTITUDE MACH NO. DELTA T 
LIFT L/D Q 
ENERGY VELOCITY TIME 
DRAG SP RANGE NOX 
242421. 23000. 
.23516 242421. 
36801. 
18485. . 01793 
240000. 
,23282 
.01786 
28000. 
240000, 
3 6801. 
18412. 
230354. 28000. 
.22346 230354. 
36801 . 
18135, 
.7500 .00 
13.115 271.3 
445.83 580.33 
.03327 .0 
.7500 10.82 
13.035 271.3 
445.88 591.14 
.03335 .0 
.01759 
.7500 
12.702 
445.88 
,03369 
43.53 
271.3 
634.68 
.0 
DELTA D DELTA F THRUST FUEL FLOW EX POW 
PCODE 
FUEL T/TMAX DIST 
ENG PAR 
3400,0 137832. 
.000 
80.4 2421. 
2 
3480.4 140253. 
,000 
9646 . 323.5 
2 
3803.9 149899. 
.000 
18485. 
.60614 
18412. 
.60376 
18135. 
.59466 
SFC 
13404. 
.72512 
13368. 
.72606 
13233. 
.72972 
DH/DT* 
2237.2 
.0 
2273.4 
.0 
2423.0 
.0 
WEIGHT 
CLIFT 
CDRAG 
230354. 
.22346 
.01759 
230350. 
.22879 
. 01762 
230313. 
.28349 
6 DESCENT 
ALTITUDE MACH NO. DELTA T 
LIFT L/D Q 
ENERGY VELOCITY TIME 
DRAG SP RANGE NOX 
28000, 
230354. 
36801. 
18135. 
28000. 
230350. 
36596. 
17740. 
28000. 
230313. 
.7500 .00 
12.702 271.3 
445.88 634.68 
.10258 .0 
.7412 ,06 
12.985 265.0 
440.65 634.74 
.10286 .0 
. 6658 
15.065 
.54 
213 .8 
DELTA D DELTA F THRUST FUEL FLOW EX POW 
PCODE 
T/TMAX DIST 
ENG PAR 
FUEL 
3803.9 149899. 
. 000 
3804.3 149903. 
.000 
3.8 37 . 
0 . 
.00000 
0. 
. ooooo 
SFC 
4346 . 
. ooooo 
4284 . 
.00000 
DH/DT* 
-3554.7 
.0 
-3436.6 
.0 
3768. -2660.7 
.02578 28417. 
835. 35402. 22287. 634.3 
11774. 1.00000 .62954 767.0 
.01882 
230273. 
.37259 
.02203 
230235. 
.54346 
.03332 
230205. 
.58839 
.03763 
230175. 
.56897 
.03568 
230139. 
.55140 
.03399 
230098. 
.53645 
.03261 
230051. 
.52432 
.03154 
229999. 
.51343 
.03060 
229939. 
.49342 
,02899 
229873 
,48512 
.02834 
229799, 
.48226 
.02810 
229719. 
.47963 
229630. 
.47721 
, 02769 
34936. 
15288. 
28000. 
230273. 
33277. 
13613. 
28000. 
230235. 
31617. 
14114 . 
26762. 
230205 . 
29957 . 
14724. 
25175 . 
230175. 
28298, 
14433. 
23591. 
230139. 
26638. 
14187. 
22013. 
230098. 
24978. 
13989. 
20444, 
230051. 
23319. 
13837. 
18875. 
229999. 
21659. 
13709. 
17256. 
229939. 
19999. 
13511. 
15690. 
229873. 
18340. 
13429. 
14146. 
229799. 
16680. 
13392. 
12598. 
229719. 
15020. 
13356. 
11044. 
229630. 
13361. 
13323. 
395.83 
.10505 
.5807 
16.915 
345,24 
.10978 
.4808 
16.312 
285.83 
.14156 
. 4495 
15.635 
268.64 
.14981 
.4415 
15.948 
265.58 
. 130B0 
.4333 
16 .222 262.37 
.11527 
.4247 
16.449 
258.81 
.10251 
.4155 
16.626 
254.83 
.09181 
.4063 
16.777 
250 .76 
.08255 
.4009 
17,019 
248.95 
.07393 
.3915 
17.117 
244.64 
.06673 
. 3806 
17.160 
239.24 
.06073 
. 3700 
17 .199 
233.95 
.05561 
.3598 
17,235 
228.77 
.05119 
635.28 
.0 
.70 
162.6 
635.98 
.0 
. 86 
111.5 
636.85 
.0 
.94 
103 . 0 
637.79 
.0 
.97 
106.5 
638.76 
.0 
1.00 
109.8 
639.76 
.0 
1.03 
112.9 
640.79 
. 0 
1.06 
115,5 
641.84 
.0 
1 .08 
117.9 
642.92 
.0 
1 .11 
122.6 
644.03 
.0 
1.13 
124.7 
645.17 
.0 
1.16 
125.4 
646.33 
.0 
1.19 
126 .0 
647.52 
.0 
1.22 
126 .6 
648.74 
.0 
3808 .1 
.000 
4.3 
0 
3812.4 
.000 
4.5 
0 
3817.0 
.000 
4.4 
0 
3821.4 
.000 
4.3 
0 
3825.7 
.000 
4.4 
0 
3830.0 
.000 
4.5 
0 
3834.5 
.000 
4.5 
0 
3839.0 
.000 
4.6 
0 
3843.6 
.000 
4.6 
0 
3848.2 
,000 
4.7 
0 
3852.8 
.000 
4 .7 
0 
3857.5 
.000 
4.7 
0 
3862.2 
.000 
4.7 
0 
3866.9 
.000 
149940. 
40. 
149980 . 
37 . 
150017. 
30. 
150047. 
31. 
150078, 
36. 
150114. 
41. 
150155. 
47 . 
150202. 
52 . 
150254, 
59 . 
150313. 
66. 
150380. 
74. 
150453. 
81. 
150534. 
88. 
150622, 
.00000 .00000 
0. 
.00000 
0. 
.00000 
0 . 
0. 
3145. -2066.9 
.00000 
2019 . 
.00000 
-1774.5 
.0 
0, 1793. -1740.1 
.00000 .00000 -1310.5 
2030. -1686.5 
,00000 .OOOOO -1638.4 
0. 2276. -1637.9 
.00000 .00000 -1587.0 
0. 2525. -1593.4 
.00000 .00000 -1535.7 
0. 2775. -1552.2 
.OOOOO .00000 -1487.1 
0. 3038. -1513.6 
.00000 .00000 -1448.7 
0. 3368. -1481.3 
.00000 .OOOOO -1461.3 
0. 3666. -1447.3 
.00000 .00000 -1381.3 
3939. -1411. 
.00000 .00000 -1329.9 
0. 4207. -1377,5 
,00000 .00000 -1301.5 
229535. 
.47498 
. 02751 
229431. 
.47288 
.02733 
229320. 
.47085 
.02717 
229200. 
,46892 
229072, 
.46654 
.02683 
228935. 
.46433 
.02665 
228789. 
.45160 
. 02577 
9486. 
229535. 
11701. 
13292. 
7923 . 
229431. 
10042. 
13262. 
6355. 
229320, 
8382. 
13232. 
4783 . 
229200. 
6722. 
13203. 
3205 . 
229072. 
5063. 
13172. 
1623 , 
228935. 
3403. 
13141. 
228789. 
1743 . 
13054. 
.3498 
17.269 
223.71 
.04734 
.3401 
17.300 
218,77 
.04394 
.3308 
17,330 
213,97 
,04093 
.3217 
17 .359 
209.29 
.03825 
.3131 
17.391 
204.85 
.03585 
.3048 
17.422 
200.50 
.03367 
.3000 
17.526 
198.44 
.03177 
1. 
127 
649 
1 
127 
651 
1 
12B 
652 
1 
128 
653 
1 
129 
655 
1, 
129 
656. 
1 
133 
658 
25 
2 
.99 
,0 
.28 
.7 
.27 
0 
31 
2 
.58 
.0 
34 
6 
92 
0 
38 
2 
.30 
0 
41 
7 
70 
0 
.44 
3 
14 
0 
4 .7 
0 
3871.6 
.000 
4.7 
0 
3876.3 
.000 
4.7 
0 
3881.0 
.000 
4.7 
0 
3B85.7 
.000 
4.7 
0 
3890.5 
,000 
4.7 
0 
3895.2 
.000 
0 
3 900 .0 
.000 
96 . 
150718. 
104 . 
150822. 
112 . 
150933. 
151053, 
151181. 
137 . 
151318. 
146 . 
151464. 
0. 4726. -1311.9 
.00000 .00000 -1246.9 
0. 4979. -1280.6 
.00000 .00000 -1220.7 
0. 5228. -1250.3 
.00000 .00000 -1195.3 
0. 5472. -1220.9 
.00000 .OOOOO -1170.4 
0. 5714. -1192. 
.00000 .OOOOO -1147.6 
0. 5955. -1165.5 
.00000 .00000 -1123.7 
0 . 6246. -1146.6 
.00000 .00000 -1130.8 
* DH/DT 
ND OP THE 
IS THE AVERAGE OVER THE 
STEP . 
STEP. THE OTHER DATA ARE INSTANTANEOUS AT THE E 
#OBJ/VAR/CONSTR SUMMARY 
FUEL RANGE VAPP FAROFF FARLDG 
SW TR SWEEP TCA VCMN CH 
168803.2 3900.0 123.5 6013. 5708. 54R79 
800.0 .000 25.00 .1210 .750 45000. 129.5 
DESIGN - TIT OPR FPR BPR TTR 
ALT THRUST SFC OVEFF CDT CDP 
2800.0 30.800 1.5000 5.9000 1.0000 
45000. 3882. .6129 .2963 1259.6 85.47 
VAPP= 123.5 
FAROFF- 6013. 
FARLDG= 5708, 
AMFOR SSFOR 
W/S T/W 
20190. 
.331 
(SLS) 
THRUST 
492252.8 7.200 40700,0 3 
VJET (CRUISE) MACH 
30.8 1673.8 
0. 4469. -1344.2 
.00000 .00000 -1273.9 
15:09:02 C17-LONG-FLOPS-IN 
C17 Long Minion 
SDFTIQN 
NPRiNT-1. 
I0PT=1. 
IANAL=3, 
NOPRD=D. 
NOISE-0, 
ICu.ii =0, 
IFITE= 0, ir-..-::;I: = l, 
ITAKCF=0, 
ILHID^O, 
6 aft 
SWTTN 
MYWTS = 9, 
UL-F-2.25, 
: PAN L67.4, 
FCOMP^O . 15, 
NETAW-2, 
ETAW=0.0, 1,0, 
CHD=33.32, 13.13, 
TOC»0.135, 0.1O7, 
.- ::.v ),301, 0.591, 
S3.- 845 . 0, 
J!" =2 7 .0. 
ARHT•3.0, 
TCHT=0.085, 
HHT=1-, 
SV'J-63 5 .0, 
SNPVT=41 ,0, 
ARV7«1 0, 
TCVT-O. 11, 
NFIN-2. 
SFlN=7">_SSi 
ARFIN=1.09, 
TRFIN3.375, 
SWPFIW=50 . 0 , 
TCFIN=0.10, 
XL=159.1, 
WF=3 L,06, 
DF--23 .00, 
NEW=4 , 
NEF=0. 
WRNG=7100., 
XNAC=12.23, 
DNAC-b .23 , 
f-JLWKX=182720,0, 
F3L.FMX. = 0 .0, 
NFLCE=3, 
CARUF-1 . , 
CARGOF=50000.0, 
SEND 
$CONFIN DKS.K7IG^460O. , 
HTVC=1.0, 
VRVC»O. LO, 
GW-U5OQG0., 
THRUST=4 5700. , 
AR '.2, 
SW-36O0.O, 
SWEEP=25. 0, 
TCA=.121, 
VCMN=0,75, 
CH'45000.0, 
S3NP 
SAEP.IN 
MVAERO=0r 
AITEK.*1.2, 
VAPPfi=115.C 
FUTO=<!400 . , 
FLLDG^3ZQ0 . 
CLTQM-3 .183 
SEND 
SEN( 3-IN 
IGENEN=1, 
IPLE-1, 
WOMEG=1, 
TXT75AP=0, 
Ll-FAC - 3 . , 
EMACH=0.80, 
S^ND 
0.75, 0,70, 0.60, 0.50, 0.40, 0,30, 0.20, 0.10, 0.0, 
SSNSRNE TENC=2, 
IFILE='TFNSEP' , 
TF TLE= ' EflGTAB' , 
OFILE='ENGOUT', 
OPKDKS=30.8, 
BPPJ3E5=5 • 9 , 
T37DES=2800 . , 
YEAR=1995. , 
IGVW=-1 , 
SEND 
SUlSSIN 
FACT=1.0 , 
ISKAL--1, 
MSUHPT^l. 
IATA=0, 
1FLAG=2 , 
IRW=1, 
ITTFF=1 TAX0TM=15.0, 
TAK0TM=2 .0, 
TAXITM=2.0, 
KCLIMB=1, 
CLMHIN=0.3, 
FWF--1•, 
IFAA£L=0, 
IFAADE=0, 
NCRUSErl . 
I0C=2, 
CRKRIN^O.3 , 
CRMACH-0.75, 
CRALT-28000. 
IVS-1, 
IRS=1, 
TTMMAP-2.0, Al/RHAN=500.0 
SEND "5 -UV 
CLIKB 
CRUISE RELEASE 
REFUEL CKMISE 
DESCENT 
END 
4J 30. 
50550. 
-2000. 
500. 
Nov j 8 96 
15;09;03 
i 
# NAMELIST SOPTION 
PROGRAM CONTROL, EXECUTION, ANALYSIS AND PLOT OPTION DATA 
DESCRIPTION NAME VALUE DIMENSIONS 
TYPE OP PROBLEM IOPT 1 
ANALYSIS OPTION IANAL 3 
MAIN ENGINE DECK SWITCH INENG 1 
DETAILED TAKEOFF SWITCH ITAKOF 0 
DETAILED LANDING SWITCH ILAND
COST CALCULATION SWITCH ICOST 0 
TRANSPORT/FIGHTER SWITCH IFITE
TAKEOFF PROFILE FOR NOISE NOPRO 0 
PROFILE OUTPUT FILE SWITCH NPFILE
NOISE CALCULATIONS SWITCH NOISE 0 
MASTER PRINT CONTROL MPRINT 1 
XFLOPS DATA PLOT SWITCH IXFL 0 
AERO POLAR PLOT SWITCH IPOLP
THRUST DATA PLOT SWITCH IPLTTH 0 
HISTORY DATA PLOT SWITCH IPLTHS C 
EXCESS POWER PLOT SWITCH IPLTPS 0 
# NAMELIST SWTIN 
GEOMETRIC, WEIGHT, BALANCE AND INERTIA DATA 
DESCRIPTION NAME VALUE DIMENSIONS 
MAX OPER MACH NUMBER VMMO .0000 
ULTIMATE LOAD FACTOR ULF 2.250C 
REF WEIGHT NUMBER NWREF 39 
CG REFERENCE LENGTH CGREFL 1909.2 
X FOR START OF CGREFL CGREFX .0 
SWITCH TO COMPUTE WEIGHTS MYWTS 0 
DESIGN GROSS WT. (RATIO) DGW 1.000 
HYDRAULIC SYSTEM PRESSURE HYDPR 3000, 
IN 
IN 
WING DATA 
DIHEDRAL(POSITIVE) DIH .000 
GLOVE AND BAT AREA GLOV -92.05 
SPAN SPAN 167.40 
CONTROL SURFACE AREA RATIO FLAPR .3330 
FRACTION OF COMPOSITES FCOMP .1500 
AEROELASTIC TAILORING FACT FAERT .0000 
STRUT BRACING FACTOR FSTRT .0000 
VARIABLE SWEEP FACTOR VARSWP .OOOC 
DEG 
SQ FT 
FT 
DETAILED WING DEFINITION DATA FOR 2 STATIONS 
STATION DATA 1 2 
0 Y/SEMISPAN ETAW 0000 1.0000 
0 CHORD/SEMISPAN CHD 32 8200 13.13O0 
0 THICKNESS/CHORD TOC 1350 . 1070 
0 LOAD PATH SWEEP SWL .00 .00 
0 REFERENCE ASPECT RATIO ARREF 7 .20 
REFERENCE THICKNESS/CHORD TCREF ,12100 
FRACTION OF LOAD ON DEFINED 
WING (OR REF WING AREA) PCTL 1.0000 
NO. OF INTEGRATION STEPS NSTD 50 
FLOPS-OUT 
ENGINE LOCATIONS 
LOAD DISTRIBUTION CONTROL 
HORIZONTAL TAIL DATA 
AREA 
1/4 CHORD SWEEP ANGLE 
ASPECT RATIO 
TAPER RATIC 
T/C 
LOCATION ON VERTICAL TAIL 
VERTICAL TAIL DATA 
NUMBER OF VERTICAL TAILS 
AREA 
1/4 CHORD SWEEP ANGLE 
ASPECT RATIO 
TAPER RATIO 
T/C 
WING FIN DATA 
AREA 
ASPECT RATIO 
TAPER RATIO 
T/C 
1/4 CHORD SWEEP ANGLE 
NUMBER OF FINS 
FUSELAGE DATA 
NUMBER OF FUSELAGES 
TOTAL LENGTH 
MAXIMUM WIDTH 
MAXIMUM DEPTH 
CARGO AIRCRAFT FACTOR 
PASSENGER COMPART LENGTH 
LANDING GEAR DATA 
LENGTH OF MAIN GEAR 
LENGTH OF NOSE GEAR 
DESIGN LANDING WEIGHT 
SET WLDG TO END OF DESCENT 
CARRIER BASED AIRCRAFT 
PROPULSION SYSTEM DATA 
NUMBER OF ENGINES ON WING 
NUMBER OF ENGINES ON FUSE 
BASELINE ENGINE THRUST 
BASELINE ENGINE WEIGHT 
WEIGHT SCALING PARAMETER 
BASELINE INLET WEIGHT 
INLET WT SCALING EXPONENT 
BASELINE NOZZLE WEIGHT 
NOZZLE WT SCALING EXPONENT 
BASELINE NACELLE LENGTH 
BASELINE NACELLE DIAMETER 
FUEL CAPACITY OF WING 
(FUEL CAPACITY FACTOR 
FUEL CAPACITY OF FUSELAGE 
ADJUST FUSE FUEL CAPACITY 
AUXIL TANK FUEL CAPACITY 
NUMBER OF FUEL TANKS 
ADDED MISC PROP SYSTEM WT 
CREW AND PAYLOAD DATA 
FIRST CLASS PASSENGERS 
TOURIST PASSENGERS 
STEWARDESSES 
GALLEY CREW 
ETAE .3010 
PDIST 2 .00 
SHT 845.00 SQ 
SWPHT 27 .00 DEG 
ARHT 5.00 
TRHT .0000 
TCHT . 0850 
HHT 1.0000 
NVERT 1 
SVT 685.00 SQ 
SWPVT 41.00 DEG 
ARVT 1.0000 
TRVT .0000 
TCVT . 1100 
SFIN 72 .55 SQ 
ARFIN 1,0900 
TRFIN .3250 
TCFIN .1000 
SWPFIN 50.00 DEG 
NFIN 2 
NFUSE 1 
XL 159.10 FT 
WF 21.06 FT 
OF 23 . 00 FT 
CARGF 1.0000 
XLP 120.01 FT 
XMLG .00 IN 
XNLG .00 IN 
WLDG 425750.0 LBF 
MLDWT 0 
CARBAS .00 
NEW 4 
NEF 0 
THRSO .0 LBF 
WENG 7100.0 LBF 
EEXP 1 .15000 
WINL .0 LBF 
EINL l.ooooo 
WNOZ .0 LBF 
ENOZ 1.00000 
XNAC 12 .23 FT 
DNAC 6.23 FT 
FULWMX 182720.0 LBM 
FWMAX 17 . 506) 
FULFMX .0 LBM 
IFUFU 0 
FULAUX . 0 LBM 
NTANK 1 
WPMISC . ooc LBF 
NPF 0 
NPT 0 
NSTU -1 
NGALC -1 
(CALC) 
BTITLE, BEGIN INPUT DATA ECHO 
C17 Long Mission 
15:09:03 Cl 7-LONG-FLOPS-OUT 
FLIGHT CREW NFLCR 3 AUXILIARY GEAR CGA1 ;., IN 
WEIGHT PsiB PASSENGER WFFAS5 165-0 uw AUXILIARY TANKS CGAUT ,0 at BAGGAGE
 PER PASSENGER 
BPP 4 . 0 LBF AMMO AND NONFIXED GUNS 1' 3"AMMO . 0 IN 
CARGO IN WING CARGOV) . U LBF MISCELLANEOUS USE?L'L LOAD ogwrs .0 IN 
CARGO :N FUSELAGE CARGOF .55008.0 l',V>? 
OVEBR1DE PARAMETERS FOR WEIGHTS (t NAMELIST SC05IFL3 
WING TOTAL FRWI 1 . 0000 GEOMEI-R ,T RATIOS, OBJECTIVE FUNCTION FACTORS, AND DESIGN VARIABLES 
WLNG WEIGHT FIRST i.-:RM FRWI1 1 .oooo 
WING WEIGHT SECOND TERM FSW12 1 . O00D DESCRIPTION NAME VAI.ise DIMENSIONS 
WING WEIGHT THlttO TERM FRWI! 1 .coou 
HOSI10NTAL TAIL FRHT 1 . oooo DESIGN RANGE. 173SRNG 
4650.0 N MI 
VERTICAL TAIL rRVT 1 .oooo KING LOADING REQUIRED WER . 00 
WING VERTICAL FIN FRfTN 1 . oooo THRUST/WEIGHT REQUIRED TWR . ooooo CAAVi RD 
FRCAN 1 .oooo 
GLOVE/WING ABBA REQUIRED 
PGLOV . ooooo 
FRFU 1 .0500 HORIZ TAIL VOLUME COEF SsTVC 
l.519969 
NOSE LANDING GEAR PPLGN 1 . oooo VERT TAIL VOLUME COEF VTVC .100000 
MAIN LANDING • *KAR FRLGM 1 .oooo COST CALCULATION OTITCH 1COST 0 
NACELLES TOTAL OB FRNA 1 oooo 
AIR INlltJCTtON SYSTEM FUNCTION TO BE OPTIMIZF.5 - OBJ = 0000* (RAMP WEIGHT) + 1.0000*FI! 
THRUST REVEP.SKRS - TOTAL WTHR .0005 •f ACHML/Q) * 
MISC PROPULSION SYSTEMS WPMSC I .0000 0DTI. 'RANGE + .0000*COST * 
FUEL SYSTEM WPSYS 1 .0000 SIONS) 
. ilRFACE CONTROLS FTRSC 1 . i
 >00 
AUXILIARY POWER UNIT WAPU - . oooo 
INSTRUMENT GROUP WIN 1 .oooo DESIGN VARIABLE DATA 
HYBHALiLICS GROUP WHYD 1 .0000 
ELECTRICAL GROUP WrILEC 1 . 0DOD VARIABLE NAME 
VALUE AC riVITY LOWER BOUND 
AVIONICS GROUP WAVOHC 1 .oooo • SCALE FACTOR 
ARMAMENT GROUP WARM .QD00 
FURNISHINUS GROUP WFURN • '00 RAMP WL-GHT, LBF GW 650000,0 0 . 0 
AIR CONDITIONING GROUT 
WAC 1 . oooo -5- .0000 0 
ANTI-ICING GROUP OR WAI 1 . oooo WING ASPECT RATIO AR 7 .7.000 0. .3333 
AUXILIARY GKAR + -00000 
UNUSABLE FUEL WUF I .oooo THRUST PER ENGtNK, LBF THRUST 40700.0 0. .000 
ENG INE 0 : 1. WOT , 1 * .ooooo PASSENGEK SERVICK GR AMMO WSRV 1 .oooo REF WING AREA, SQ FT SW iBOO.0 0. .0 
AND NONFIXED WEAPONS 
+• ,00000 
CARGO ANU EA-:JCAGE CONTAIN. 
WCON 1 .0000 WING TAPER RATIO TR .0 70:77! 0. .03000 
OR MISCEIL. USEFUL LOAD 4- .ooooo 
AUXILIARY FUEL TANKS WAUXT 1 oooo WING 1/4 CHORD SW^P, DEG SWEEP 25 . 0C 3 . .00 
FLIGHT CREW AW:) BAGGAGE WFLCHB 1 .oooo * , ooooo 
OAHr.n CREW AND BAGGAGE 
WSTUAB 1 ,ooo
WING T/C 
TCA .12100 0. ,00003 
+ .00300 
HORIZONTAL CENTER OF GRAVITY DATA CRUISE M-'.CH NUMBER VCMN ,75000 0. .00300 
WING CGW .0 IN + .00000 
HORIZONTAL TAIL CCMT .0 IN 
MAX CBL'ISE ALTITULS, FT 
CH 45000.0 0. .0 
• . 'ICAL TAIL CGVT .0 IN .00000 
WING VERTICAL FINS GCrIN . 0 IN TURBINE INLST TEMP (R) ETIT .00 0 . .00 
CANATD CGCAN .0 IN + .QQQO0 
FUSELAGE CGF .0 IN OVERALL PR INSURE BAT50 EOPR .000 0, .357 
NOStt lAPfllTNG GEAR ,GN .0 IN + .ooooo 
MAIN LANDING OEAft CGLGM . 0 IN FAN PRESSURE RATIO EFPR , oooo 0. .0000 
TWO FORWARD ENGINES CGEF . 0 IN t .3 0000 
ONE OR TWO APT ENGINES 
CUE A .0 IN BYPASS RATIO EBPR . oooo 0. .3000 •JXILIA3Y POWER ON [T CGAP . 0 IN -5- . ooooo AVI:.-.M 11 :s
 GROUP 
CGAV .0 IN THROTTLE RATIO ETTR .3 07 53 0. ,00000 
ARMAMENT GROUP CGARM ,0 IN + ,ooooo 
FLIGHT CREW CGCR .0 IN 
PASSEWSEKS CUP . 0 IN 
CARGO.'EXT STORES IN WING 
cijCW ,0 IN 
CARGO/EXT STORES IN FUSE CGCF .0 IN # NAMELIST SAEaiN 
FUSfitJh(J£ FUEL CUZWF . 0 IN AFKUDYNAMIC OPTIONS AND APPROXIMATE TAKEOFF , LANDING PATA 
WING FUEL CGFWt , c IN 
AIR INDUCTION SYSTEM 
i V;N .0 IN DESCRIPTION N.WE DIMENSIONS AIR CONDITIONING CGAC .0 IN 
.oooo-
. o 
. oooo 
.OOC 
. 0 
.ooooo 
.00 
.33000 
. ooooo 
. 0 
.00 
.000 
. oooo 
.oooo 
. 00550 
Nov 18 96 
15:09:03 
AERODYNAMIC INPUT METHOD 
WAVE DRAG INPUT SWITCH 
WAVE DRAG FACTOR 
LINEAR/PARABOLIC INTERP 
AERO MATRIX FORMAT SWITCH 
MAX CAMBER AT 70 PERCENT 
SEMISPAN 
AIRCRAFT BASE AREA 
WING TECHNOLOGY 
MODIFY EDET DATA 
FIXED DESIGN CL 
TURBULENT/LAMINAR FLOW 
AERO EFFICIENCY FACTOR 
KYAERC 
IWAVE 
FWAVE 
ITPAER 
IBO 
CAM 
SBASE 
A ITER 
MODARO 
FCLDES 
XLIAM 
E 
0 
0 
1,0000 
2 
0 
.00000 PERCENT CHORD 
.0 SQ FT 
1.2 
0 
-1.0000 
.0 
i. oooo 
OVERRIDE PARAMETERS FOR WETTED AREAS 
WING WETTED AREA SWETW 1.0000 
HOR. TAIL WETTED AREA SWETH 1.0000 
VERT. TAIL WETTED AREA SWETV 1.0000 
FUSELAGE WETTED AREA SWETF 1.0000 
NACELLE WETTED AREA SWETN 1.0000 
TAKEOFF AND LANDING DATA 
RATIO OF MAX, LANDING WT. 
TO MAX. TAKEOFF WT. WRATIC 
MAX. LANDING VELOCITY VAPPR 
MAX. TAKEOFF FIELD LENGTH FLTO 
MAX. LANDING FIELD LENGTH FLLDG 
MAX. CL TAKEOFF CONFIG. CLTOH 
MAX. CL LANDING CONFIG. CLLDM 
APPROACH CL CLAPP 
AIR DENSITY RATIO DRATIO 
L/D RATIO 2ND SEG. CLIMB ELODSS 
L/D RATIO MISSED APPROACH ELODMA 
THRUST PER ENGINE TAKEOFF THROFF 
THRUST PER ENGINE 2ND 
SEG. CLIMB THRSS 
THRUST PER ENGINE MISSED 
APPROACH THRMA 
.6550 
115.OOOC 
4400.0 
3200.0 
3 .5850 
3 . 0000 
,0000 
1 .0000 
.0000 
.0000 
.0000 
KTS 
FT 
FT 
.0 LBF 
.0 LBF 
It NAMELIST SENGDIN 
ENGINE DECK CONTROL, SCALI1 
DESCRIPTION 
ENGINE DECK PRINT CONTROL 
ENGINE DECK SOURCE SWITCH 
SLOPE FACTOR FOR 
EXTRAPOLATING FUEL FLOWS 
SUBSONIC FUEL FLOW FACTOR 
SUPERSONIC FUEL FLOW FACT 
FLIGHT IDLE SWITCH 
IGNORE NEGATIVE THRUSTS 
MIN IDLE FUEL FLOW FRACT 
MAX IDLE FUEL FLOW FRACT 
SFC EXTRAPOLATION SWITCH 
PART POWER DATA SWITCH 
MAX. CRUISE POWER SETTING 
BOOST ENGINE SWITCH 
FUEL FLOW SCALING 
CONSTANT TERM 
FUEL FLOW SCALING 
LINEAR TERM 
NITROGEN OXIDES SWITCH 
INSTALLATION DRAG SWITCH 
AND USAGE DATA 
NAME VALUE DIMENSIONS 
NGPRT 1 
IGENEN
EXTFAC 1.0000 
FFFSUB 1.0000 
FFFSUP 1.0000 
IDLE 1 
NONEG
FIDMIN .0800 
FIDMAX 1.0000 
IXTRAP 0 
IFILL 2 
MAXCR
BOOST .0000 
DFFAC .0000 
FFFAC .0000 
NOX 0 
INSDRG 0 
FLOPS-OUT 
MACH NUMBERS AND ALTITUDES FOR ENGINE DECK GENERATION 
ALTITUDES 
,80 
.75 
.70 
.60 
.50 
.40 
.30 
.20 
.10 
.00 
-1 . 
-1 . 
-1. 
-1 . 
-1 . 
-1 . 
-1 . 
-1 . 
-1 . 
-1 . 
It NAMELIST SENGINE 
ENGINE CYCLE ANALYSIS INPUT DATA 
DESCRIPTION VALUE DIMENSIONS 
2-COMP SEP FLOW TURBOFAN 
ENGINE CYCLE DEF. FILE 
I ENG 
IFILE 
2 
TFNSEE 
COMPONENT MAP TABLES FILE TFILE ENGTAB 
PRINT LEVEL INDICATOR IPRINT 
PRINT VIB/ANOPP DATA NPRINT 
PRINT LEVEL FOR WEIGHTS IWTPRT 
PLOT ENGINE SCHEMATIC IWTPLT 
CYCLE ANALYSIS OUTPUT FILE OFILE 
1 0 1 
0 
ENGOUT 
FLAG TO GENERATE A DECK GENDEK F 
SWITCH FOR WEIGHT CALCS NGINWT 0 
(0=NONE, 1=ENGINE, 2=1 + INLET, 3=2 +NACELLE 
PART POWER DATA CONTROL ITHROT 
NUMBER OF A/B POINTS NPAB 
NUMBER OF DRY POINTS NPDRY 
PART POWER THRUST CUTOFF XIDLE 
MAX ALLOWABLE ITERATIONS NITMAX 
4=3+NOZZLE| 
1 
0 
15 
.05000 
50 
DESIGN POINT DATA 
DESIGN POINT NET THRUST DESFN 40700.0 
OVERALL PRESSURE RATIO OPRDES 30.8000 
FAN PRESSURE RATIO FPRDES 1.5OO0 
BYPASS RATIO BPRDES 5.9000 
DESIGN TURBINE INLET TEMP TETDES 2800.0 
DESIGN THROTTLE RATIO TTRDES 1.OOOC 
DEG R 
OTHER ENGINE CONFIGURATION DEFINITION DATA 
FLAG FOR AFTERBURNER ABURN F 
FLAG FOR DUCT BURNER DBORN F 
AFTERBURNER EFFICIENCY EFFAB .85000 
MAX AFTERBURNER TEMP TABMAX 3500.0 DEG R 
FLAG FOR VARIABLE NOZZLE VEN F 
CUSTOMER COMPRESSOR BLEED COSTBL 1.0000 LB/SEC 
TURBINE COOLING {FROM HPC) WCOOL -.0001 FRACTION (OR T41 R] 
CUSTOMER POWER EXTRACTION HPEXT 200.0C HP 
FUEL HEATING VALUE FHV 18500.0 BTU/LB 
TECHNOLOGY AVAILABILITY YEAR 1995 . YEAR 
FLAG TO DO BOATTAIL DRAG BOAT F 
DELTA TEMPERATURE DTCE .00 DEG C 
DTCE VARIES TO ZERO AT ATC 10000. PT 
FLAG TO DO SPILLAGE DRAG SPILL F 
FLAG TO DO LIP DRAG LIP F 
C17-L0NG-
USPJl TO DEFINE MACH-ALTITUDE ARRAY POINTS 
MAX I MIM KACH NUMBER 
:• .7S0Q 
MAX I SUM ALTtTUPE . . IAS 450OC-.il FT 
INCREMENT IN MACH NUNEER XMINC .2000 
IWlOkKPlBNT IN ALT1TWB AIHC 5000.0 FT 
MINIMUM DYNAMIC PRESSURE (.: N 150.00 PSF 
MAXIMUM DYNAMIC PRESSURE O.MAX 1200.00 PSF 
ENGINE CYCLE OPTIMIZATION CRUISE CONDITION 
MACH NUMBER XMDE3 .7500 
ALTITUDE XADKS 45000.0 KT 
ENGIS'L CYOI.H: BEHAVIORAL CONSTRAINTS 
MAX COMPRESS DISCHARGE TMP CtTlVOt 39999 . DDDO R 
KAX C0MPRE3R DISCHAKQE PRS CBPMAX 99995.0000 PSI 
MAXIMUM JET VELOCITY V..TMAX ¥9J39.OOOO FT.-'SEC 
MINIMUM SPECIFIC THRUST STMIN 1.0C-C0 LB/L3/SEC 
MAXIMuH BYPASS/COHE AREA AHMAX 99999.COOD 
Sl-ii LEVEL STATIC MAXIMUM THRUST 40700.0 I.S 
GENERATED PROPULSION SYSTEM V.'T. 71O0.0 LB 
(NEW BASELINE ENGINE THRUST - OVERRIDES THRSO) 
# ALL POINT KJfGINE DECK SUMMARY 
MACH = .,<OD, ALTITUDE - 40000., THRUSTS / FUEL f'LGtfS/SFUS.'NOX RATIOS FOLLOW 
5064.B 4405.2 3779.3 3469.7 3169.2 Zfi'M.i 23.'.5.6 2244.9 1977.3 17JP.0 
0502.4 1233.9 01OJ.2 917.3 742.fi .0 
3182.3 2821.3 2489.9 2331.6 2130.8 2( 5.4 1872.7 1731.9 1601.6 1480.9 
135B.5 12*5.0 1168.4 1077,2 9*1.9 629,3 
.62!) .640 .659 .672 .688 .710 .739 .771 .810 .856 
.911 .978 1.009 1.174 1.030 .000 
MACH -= .800, ALTITUDE = 35000., THRUSTS/FUEL FLOWS/SFC5/NOX FA'.-rOS FOLLOW 
6447.8 9608.1 4811.3 4417.2 4034.6 3630.6 3228.0 2357.9 2517.J 2202.4 
0012.7 1047.2 1-SU1.4 1163.5 945.6 .0 
OOOO..' 3576.7 3172.1 2970.R 2778.7 2560.6 238*".0 2206.7 2 0(10.7 0686.8 
1744.1 J61-.H 14 08.7 1172.5 1263.7 P.01.8 
.629 .641 .659 .673 .689 .711 .739 .772 .8.11 .857 
.912 .V<3 1.060 1.175 1.336 .000 
MACH - .BOO, ALTITUDE = 30000., THRUSTS/FUEL PLOWS/SFC5/NCX RATIOS FOLLOW 
B1S3.4 7100.2 6091.4 5592.5 SlO'A.l 4596.6 4086.6 3616,3 3187.0 2738.3 
2421.6 2085.5 1778.1 14-7,4 lis/.2 .0 
5251.2 4655.4 4103.7 3347.4 3593.6 3342.1 3090.0 2357.8 2642.9 2443.6 
225R.8 2037.4 1920.1 1777.5 lb36.6 1038.4 
,643 .656 .675 .688 .704 .727 .756 .790 .329 .376 
.933 1.O01 1.081 1.202 1.367 .000 
MACH - ,1170, ALTITUDE = 25000., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
10227.4 8395.4 7611.6 7D0S.5 6099.6 5758.8 5120.1 4533.2 3990.8 3453.3 
3D33.9 2612.7 2227.6 1853.1 1099.9 .0 
6710.3 5966.7 5265.9 4931.1 4512.2 4283.0 3960.5 0440.8 33B7.3 3131,9 
2895.0 2675.3 2471.1 2278.2 2.397.5 1330.9 
.«5B .671 .690 .704 .701 74 4 .774 . SOB . "lis .897 
.944 1.024 1.109 1.220 1.300 .000 
MAC!: = .804, ALTITUDE = 20rJO0,, THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
J.2701.3 11047.1 94,7.6 8701.3 7947 b 7 151 . fl 620H.6 560 9.7 495H.6 433 3.3 
3/67.7 44 4.7 2766.5 23 01.7 1862.7 ,0 
8550.0 7579.9 6639.7 6204.4 3359.3 5441.4 5401.3 4 653.1 4303.1 -J73.6 
3677.6 3398 . 7 3139.2 2B94.1 2664 6 1690 .B 
.'073 .01 0 .706 .700 .737 .761 .791 .827 .868 .917 
.976 1.044 1.135 1.257 1.431 .OOQ 
MAC'.! = ,600, ALTITUDE - 150OO., THKJSTS.'FUEL FLOWS/SPCS-'NOX RATIOS FOL.L.UV4 
10653.7 136J5.0 11580.6 1D723.9 9795.0 9314.2 7S36.7 6938.4 6111.2 5346.3 
FLOPS-OUT 
* 4643.6 3999.0 J409.6 2636.7 2295.7 ,0 
10777.2 5454.4 8432-3 7396.2 73B5.5 6859,1 6342.6 5865.2 5424.0 5015.0 
+ 463 5.8 4244.0 3957,0 3648.0 2358.'/ 2131.2 
. 5BE .702 .722 .736 .'• '4 .77H .809 .845 . J 0 b .938 
+ .998 1.071 1.161 1.286 1.4B3 .000 
MACH = .800, ALTITUDE = 1000D., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
17885.7 15556.3 13346,1 12252.9 11191.6 10071.0 8*54.0 7927.7 6980.6 6109.1 
* 5005.7 4565.2 3B95.7 3241.2 2623.0 .0 
12677.3 11239.4 3913.4 9288,7 8636.0 3068.8 7460.4 6899.6 6380.5 5S99.0 I
 5453.4 5.19.0 4GS4.8 4291.4 3151.1 2507.0 
.709 .723 .743 .758 .7TG .801 .833 .370 .314 ,966 
* 1.02B 1.103 1.195 1.324 1,506 .000 
MACH :• .800, ALTITUDE -. 5000., TKHOSITS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
18913.5 16450.2 14113.1 32957.0 11834.B 10649.7 9468.7 8343.2 7383.8 5460.2 
+ 561D.6 4631.3 4113.5 3027.5 2773.3 .0 
13364.6 12371.3 1O918.0 10224 . 1 9552.9 B831.4 (211.7 7594 . 4, 7023.1 6410.6 
+ 0002,'0 L04'.'.O 0120.6 472^ 0 404^.0 2759-5 
.738 ,752 .774 .789 .808 .334 .867 .906 .951 1.005 
+ 1.070 1.14B 1.244 1.378 1.568 .000 
MACH = .BOO, ALTITUDE • O., THHljSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
19837.8 17254.1 10nC2.R 135^0.3 12413.3 11170,2 9931.4 8792,9 7744.7 6775.9 
+ 0304.7 501.7.9 43JC.9 3595.0 2909.3 .0 
15315.2 13577.5 11982.9 11221.0 10495.4 9747.4 9012-4 8334.9 7707.9 7126.7 
+ 6587.8 f08/.9 5523.2 5134.1 477i,0 302B.G 
.772 .787 ,810 .826 .846 .873 .907 .948 .995 1.052 
+ 1.119 1.01 1.301 1.442 1.640 .000 
MACH = .750, ALTITUDE = 40000., THKUSTS/FUEL FLOWS/MCA/NOX RATIOS FOLLOW 
4941.1 4295.4 3696.3 3390.8 3103.5 2798.1 2193-4 2232.3 3051.5 J'/IO.B 
» 1489.5 1286.7 110O.4 903.2 736.7 .0 
3006.4 2665.3 2342.4 2204.0 2052.9 1917.2 1773.8 1641.1 1508.1 1404.0 
+ 1293.2 1200.0 1303.4 1020.7 939.3 592.0 
. GOd .620 .638 .650 .665 .585 .711 .742 .778 .623. 
* .872 .50 3 1.00/ 1.124 1.27r'. .000 
MACH = ,750, ALTITUDE = 3^000., THRU14TS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
8290.5 545B.6 4693.7 4316.J 3951.1 556:.3 3X74.4 2816.6 2434.5 2178.1 
+ 1096-3 1633.2 1400.9 1156.2 937.9 
3329.6 3395.-1 2996./ 0!")7.7 2623.0 2442.3 2259.6 2090.6 1933.9 1788-6 
- 1653-8 1523.6 1412.0 1300.3 1197.2 754,2 
.609 .621 .633 .650 .665 .686 .712 .742 .778 .821 
t .872 .933 1.00S 1.125 1.276 .000 
MACK • .710, ALTITUDE - .0000., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
7964.6 6923.9 4442.9 0465.7 501)2.6 4510.4 401 9.0. 3066.0 1H0.7 0 -7.7 
+ 2401.0 2074.1 1773,7 LltJ.9 1187.5 .0 
4959.7 4197.0 3330.8 3636.1 3403.3 3162.B 2926.3 2707.4 2504.5 2316.3 
* 2141.7 1979.6 1328.6 1=83.9 1350.4 976.7 
.623 .635 .C53 .665 .680 .701 .728 .759 .796 .040 
+ .892 .954 1.030 1.150 1.306 .0 N 
MACH - ,750, ALTITUDE - 25000., T] I RUSTS / Flip. I. F I. OWE/ SFCS/NOX RATIOS FOLLOW 
997B.0 S671.2 7445.1 6847.3 6267.2 5650.5 5035.2 4467.6 3940.9 3454.8 
+ 3007.9 259B.4 3222.0 1833.9 10B7.7 .0 
6355.7 5634.6 4973.1 0659.5 0361.2 4053.0 3749.9 3469.4 3209.4 2968.2 
* 2744.5 2530.0 2343.2 2157.9 1986.3 1251.5 
.637 .65D ,668 .680 .696 .717 .745 .777 .814 .859 
f .912 .976 1.035 1.177 1.335 .000 
:A!I! = ,750. W.TITLT-K = 20000,, TO IRUSTS / EU Et FLOWS / SFCS/NOX RATIOS FOLLOW 
123BB.2 10769.4 9243.5 n501.3 7781.0 7015.5 6251.5 5546.3 0802.9 42S3.1 
* 3714.5 3226.1 2758-8 2276.9 1847,1 ,0 
B07'i.a 7155.1 63J5.1 5916.9 5538.1 5146.7 4761.8 4414J.7 4075.4 0769.2 
<• 3435.1 3321.4 2975.5 2740.2 2522. S 1589.3 
Nov IS % 
15:09:03 C17-LONG-FLOPS-OUT 
.651 .664 .683 .696 .712 .734 
.933 .999 1.079 1.203 1.366 .000 
.762 .794 , 833 
MACH .750, ALTITUDE 15000., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS 
15263.4 13269.0 11388.9 10474.4 9587.0 8643.7 
4601.3 3374.8 3399.1 2805.4 2275.7 .0 
10169.0 9015.2 7956.8 7455.1 6977.8 6484.7 
4391.2 4058.8 3749.1 3452.6 3178.8 2002.4 
.666 .679 .699 .712 .728 .750 
.954 1.021 1.103 1.231 1.397 .000 
7702.4 6834,2 6028.5 
5999.8 5551.0 5134.9 
.779 ,812 .852 
MACH = .750, ALTITUDE = 10000., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS 
18359.2 15960.2 13698.8 12598.9 11531.4 10396,8 9264.7 S220.3 7251.2 
5534.5 4781.0 4088.5 3374.4 2737.3 .0 
12525.0 11103.9 9800.3 9182.3 8594,5 7987.2 7389.9 6837.1 6324.6 
5408.5 4999.2 4617.7 4252.5 3915.3 2466.4 
.682 .696 ,715 .729 .745 .768 .798 .832 ,872 
.977 1.046 1.129 1.260 1.430 .000 
MACH .750, ALTITUDE 5000. THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS 
19452.9 16911.0 14514.9 13349.5 12218.4 11016.2 
5864.3 5065.9 4332.1 3575.4 2900.4 .0 
137B4.7 12220.7 10785.9 10105.9 9458.9 8790.5 
5952.5 5502.0 5082.1 4680.2 4309.1 2714.4 
.709 .723 .743 .757 .774 .798 
1.015 1.086 1.173 1.309 1.486 .000 
9816.6 8710.0 7683.2 
6133.1 7524.8 6960.7 
.829 .864 .906 
MACL .750, ALTITUDE 0. , •THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS 
20470.4 17795.5 15274.0 14047.7 12857.5 11592.4 10330,0 9165,6 8085.0 
6171.0 5330.8 4558.7 3762.4 3052.1 .0 
15127.5 13411.0 11836.6 11090.2 10380.2 9646.7 8925.3 8257.7 7638.7 
6532.3 6037.9 5577.2 5136.0 4728.8 2978.8 
.739 .754 .775 .789 .807 .832 .864 .901 .945 
1.059 1.133 1,223 1.365 1.549 .000 
MACH = .700, ALTITUDE = 35000., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS 
6166.7 5374.1 4634.6 4275.4 3922.3 3542.8 3167.0 2817.0 2492.5 
1918.0 1665.6 1415.4 1174.2 956.5 .0 
3628,4 3217.6 2844.6 2665.9 2495.2 2317.6 2144.0 1982.9 1833.6 
1566,5 1447.0 1333,7 1227.2 1128.0 692.5 
.588 .599 .614 .624 .636 .654 .677 .704 .736 
.817 .869 .942 1.045 1.179 .000 
MACH = .700, ALTITUDE = 30000, 
7807.7 6804.1 5867.9 5413.0 4966.0 4485,6 
2423.4 2108.8 1792.0 1486.7 1211.0 .0 
4698.3 4166.4 3683.3 3452.0 3230.9 3001.0 
2028.5 1873.7 1726.9 1589.0 1460.6 896.7 
.602 .612 .628 ,638 .651 .669 
.835 .889 .964 1.069 1.206 .000 
THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS 
4009.8 3566.6 3155.8 
2776.2 2567.6 2374.2 
.692 .720 .752 
MACH = .700, ALTITUDE = 25000., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS 
9781.4 3524.2 7351.3 6781.5 6221.4 5619.5 5023.4 4468.2 3953.6 
3042.3 2641.9 2245,0 1862.5 1517.1 .0 
6020.4 5338.9 4719.8 4423.5 4140.1 3845.5 3557.4 3290.1 3042.3 
2599.3 2401.0 2212.9 2036.2 1871.7 1149.0 
.615 .626 .642 .652 .665 .684 .708 .736 .770 
.354 .909 .986 1.093 1.234 .000 
MACH = ,700, ALTITUDE = 20000., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS 
12141.8 10581.1 9125.2 8417.9 7722.7 6975.5 6235.6 5546.4 4907.6 
3776.4 3279.4 2786.8 2311.9 1883.2 .0 
7642.7 6777.5 5991.7 5615,4 5255.8 4881.8 4516.0 4176.7 3862.1 
3299.7 3048.0 2809.2 2584,9 2376.0 1458.6 
.629 .641 .657 .667 .631 .700 .724 ,753 .787 
.874 ,929 1.008 1.118 1.262 .000 
.879 
FOLLOW 
5284.9 
4749 .1 
.899 
FOLLOW 
6356.8 
5849.4 
.920 
FOLLOW 
6735.5 
6437 .7 
.956 
FOLLOW 
7087 .8 
7064.8 
. 997 
FOLLOW 
2193 .2 
1695.0 
. 773 
FOLLOW 
2776.8 
2194 .9 
. 790 
FOLLOW 
3478 .8 
2812.5 
.808 
FOLLOW 
4318.2 
3570.4 
, 827 
MACH = .700, ALTITUDE = 15000., THRUSTS/FUEL FLOWS/SFCS/NOX 
14954,8 13032.5 11239.4 10368.1 9511.8 8591.6 7680.3 6831.4 
4651.3 4039.2 3432.4 2847.5 2319,5 .0 
9625.3 3535.7 7546.0 7072.2 6619.2 6148.2 5687.5 5260.2 
4155.7 3838.6 3538.0 3255.5 2992.4 1837.0 
.644 .655 .671 .682 .696 .716 .741 
.893 .950 1.031 1.143 1.290 .000 
RATIOS FOLLOW 
6044.6 5318.7 
4864.0 4496.6 
.770 .805 ,845 
MACH = .700, ALTITUDE = 20000., THRUSTS/FUEL FLOWS/SFCS/NOX 
18287.1 15936,5 13743.8 12678.4 11631.3 10506.1 9391.7 8353.7 
5687.8 4939.3 4197.2 3482.1 2836.3 .0 
12032,7 10670.6 9433.4 8841.0 8274.8 7685.9 7110.0 6575.9 
5195.1 4798.7 4422.9 4069.7 3740.9 2296.5 
.658 .670 .686 .697 .711 .732 .757 .787 
.913 .972 1.054 1.169 1.319 .000 
MACH = .700, ALTITUDE = 5000., THRUSTS/FUEL FLOWS/SFCS/NOX 
20066.7 17487.3 15081,2 13912.2 12763.2 11528.4 10305.6 9166.6 
6241.3 5419.9 4605.7 3820.9 3112.3 .0 
13629.5 12086.6 10685.2 10014.2 9372.8 8705.9 8053.5 7448.5 
5884.5 5435.5 5009,8 4609.7 4237.3 2601.2 
.679 .691 .709 .720 .734 .755 .761 .813 
,943 1.003 1.088 1.206 1,361 .000 
MACH = .700, ALTITUDE = 0., THRUSTS/FUEL FLOWS/SFCS/NOX 
21196.2 13471,7 15930.2 14695.3 13481.6 12177.4 10885.7 9682.6 
6592.6 5725.0 4864.9 4036,0 3287.5 .0 
14960.7 13267.1 11728.8 10992.3 10288.3 9556.2 8840.1 8176.0 
6459.2 5966.4 5499,1 5060.0 4651.1 2855.3 
.706 .718 .736 .748 .763 .785 .812 .844 
,980 1.042 1.130 1.254 1.415 .000 
MACH = .600, ALTITUDE = 30000. 
7718.9 6780.6 5898.1 5443.6 5010.5 
2494,1 2128.5 1782.4 1472.0 1196.9 
4290.4 3812.0 3375,9 3154,9 2946,1 
1808.4 1657,8 1517.4 1387.7. 1268.6 
.556 .562 .572 .580 .588 
.725 .779 ,851 .943 1.060 
THRUSTS/FUEL FLOWS/SFCS/NOX 
4535.4 4067,4 3629.5 
,0 
2726.2 2514.0 2317.2 
750.4 
.601 .618 .638 
.000 
MACH .600, ALTITUDE 25000. THRUSTS/FUEL FLOWS/SFCS/NOX 
9670.4 8494.8 7389.2 6819.8 6277.1 5682.0 
3124,7 2666.6 2233.0 1844.1 1499.5 .0 
5498.0 4884.9 4326.1 4042,9 3775.3 3493.5 
2317.3 2124.4 1944.S 1778.2 1625.6 961.6 
.569 .575 .585 .593 .601 .615 
.742 .797 .871 .964 1.084 .000 
5095.7 4547.0 
3221.6 2969.3 
. 632 
MACH = .600, ALTITUDE = 20000., THRUSTS/FUEL FLOWS/SFCS/NOX 
12001.5 10542,5 9170.5 8463.8 7790.3 7051.7 6324.1 5643,2 
3877.9 3309.4 2771.3 2288.7 1861.0 .0 
6978.0 6199.9 5490.7 5131.2 4791.5 4434,0 4088.8 3768.7 
2941.1 2696.2 2467.9 2256.9 2063.2 1220.4 
,581 .588 .599 .606 .615 .629 .647 
.758 .815 .891 .986 1.109 .000 
.668 
MACH = .600. ALTITUDE = 15000., THRUSTS/FUEL FLOWS/SFCS/NOX 
14773.5 12977.5 11288.5 10418.6 9589.6 8680.4 7784.7 6946.6 
4773.6 4073.8 3411.4 2817,3 2290.8 .0 
8782.4 7803.1 6910.5 6458.1 6030,6 5580.6 5146,1 4743.2 
3701.7 3393.5 3106.1 2840.5 2596.7 1536.0 
.594 .601 .612 ,620 .629 .643 .661 .683 
.775 .833 .911 1,008 1.134 ,000 
MACH - .600, ALTITUDE = 10000., THRUSTS/FUEL FLOWS/SFCS/NOX 
18055.3 15860,3 13796.2 12733.0 11719.9 10608.7 9514.0 8489.6 
5834.0 4978.7 4169,2 3443.1 2799.7 .0 
RATIOS FOLLOW 
7391.5 6503.8 
6080.6 5621.3 
.823 .864 
RATIOS FOLLOW 
8110.8 7136.7 
6887.5 6367.2 
,849 .892 
RATIOS FOLLOW 
8567.4 7538.5 
7560.2 6989.1 
.882 .927 
RATIOS FOLLOW 
3219.0 2841.2 
2134,4 1965.2 
.663 .692 
RATIOS FOLLOW 
4032.8 3559.5 
2735.1 2518.4 
.678 .708 
RATIOS FOLLOW 
5005.0 4417.6 
3471.3 3196.3 
.694 .724 
RATIOS FOLLOW 
6161.0 5437.9 
4369.0 4022.8 
.709 .740 
RATIOS FOLLOW 
7529.6 6645.9 
Nov 18 96 
15:09:1)3 CI 7-LONG-FLOPS-OUT 
10971.B 9748-4 8613.3 6049.0 7533.9 6971.7 6129.0 5925.7 545B.2 5025.7 
1524.5 1239.4 3BBD.4 3548.6 3244.1 19IB.9 
,606 .615 .626 .634 .643 .657 .676 .655 .523 ,756 
.793 .852 .931 1.031 1,159 .350 
MACH = .600, ALTITUDE = 5000., 1'HRUSTS 'FUFT FLOWS/SFCS/NOX RATIOS FOLLOW 
2150B.6 18893.9 16434.9 I516S.4 13951.5 12637.8 11333.7 10113.4 8969.7 7911.0 
6919.9 5931.0 49*6.6 4101.7 3335.2 .0 
U363.fi 11678,0 10519.3 9830.6 9179.B 3494.8 7333.5 7220.2 6650.6 6123.6 
5634.9 5166.6 4728.1 4323.9 395L.B 233B.2 
.£22 .629 .640 .648 .65B .672 .691 ,714 .741 .773 
.811 .371 .952 1.054 1.185 .000 
MACN = .500, M/MVPE t 5., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
22932.0 20144-2 17522.5 16172.2 14385.4 134/4.1 13083.7 15782.7 9563.3 3140.9 
7489.3 6323.5 5295.3 4373.1 3555.9 .0 
14695.6 13054.2 11561.0 10B04.0 10083.9 9336.0 8509.2 7935.2 7309.1 6730.0 
6192.7 =577, 1 5196.3 4752.31 4344.2 2565.7 
.611 .646 .660 .635 .678 .633 .712 .736 .764 .797 
.816 .898 .981 1,087 1.222 .353 
3ACH t .500, ALTITUDE = 20OOO., i5-IKUSTS/F3:FL ••'LOWS/SFCS/NOX RATIOS FOLLOW 
1.5279.6 10898.1 9607.3 SB76.8 3171.1 7390.0 6623.2 5922.0 3270. 0 4669.2 
4547.4 3417.9 2878.4 2371.0 1917.6 .0 
6523.6 S80B.6 5156.3 5797.4 4456.8 4098.6 3750.5 3441.5 31.5 1.4 2883.4 
2628.9 23*1.2 2163.8 596/.0 1730.6 992.1 
.331 .333 .537 .540 .545 .555 .567 .581 .598 .618 
.650 .694 .754 .83( .929 .000 
HACH =t .500, A23TITUDE = 15000., TFlHUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
15110.5 13410.8 13822.1 10923.2 10054.8 9D93.6 5556.2 7257,2 6484.9 5-45.5 
1940.5 1242.8 3512.0 2917,6 2359.7 .0 
3207.6 7303.0 648B.O 6035.8 5607.3 •" . •' 1.6 4726.2 4329.9 3964.9 3627,8 
3307.5 3003,4 2727.9 2474.8 2240.2 121S.2 
,511 .545 .549 -553 .558 .D57 .579 ,594 .611 .525 
,664 .709 .771 ,818 .949 .350 
HACH = .500, ALTITUDE - 1O0OO., THRUSTS/FUEL / SK5".=:.T73X RATIOS FOLLOW 
13456.3 153B0.3 14439.7 13341. -j 15253.1 11107.1 9952,2 8900.8 7920,8 7017.8 
6033.2 5182.3 4326.2 3563.7 2932.2 .0 
10247.5 9121.4 8105.5 7535.9 7000.9 6438,2 5900.8 5406.0 4950.3 4529.4 
4129.6 3756.2 34UB.3 J055.3 2797.0 1553.5 
.555 .557 ,561 .565 .570 .580 .592 .607 .625 .645 
.679 5/35 .783 .867 .970 .000 
MACH .500, ;-.,TT5.7DE ^ 5533., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
22 '.- 7. 7 39869.3 17515.5 161 3.3.7 54 R 57.5 13 473.0 12 084. I 10795.7 9606.0 8512.6 
7379.0 6236.1 5247.7 4322.8 3496,1 .0 
12703.7 31311.-; 10042.1 9342.2 8679.0 7931.4 'S\:.2 6701.8 6136.8 5615.1 
5119.4 4156.5 '•.225.3 3830.5 3467.4 1932.0 
567 .569 .573 .577 .083 .592 .605 .521 .639 ,SCO 
.694 .7',1 ,805 .886 .992 .000 HACT;
 = .553, Ai.'i :V. T 5., THRUSTS / FUEL FLDWS/SFCS/NOX RATIOS FOLLOW 
24956.3 22119.2 19525.2 IB010.7 16606.4 15018,9 13470.7 12035.5 10710.5 94S9.3 
8225.7 7007.4 5849.5 48JE.B 3397.2 .0 
14430.5 12B93.5 11445,7 10646.3 9893.9 9C97.8 8338.4 7639.1 6993,1 6400.5 
5835.1 5307.8 4816.3 4366.2 3353 1 2205 2 
.560 582 .536 .590 .5 >6 .'706 .619 .635 .653 .674 
.709 .757 .B23 1.014 .000 
MACH -' .400, ALTITUDE = 10000., THaL'STS/FUSL FLOWS/SFCS/NOX RATIOS FOLLOW 
19388.G 17374, S 15462.0 14297.1 13170,0 11919.3 I0TO4.3 9577,1 8534.5 71iJ6,4 
611B.2 5489.0 4620.9 3793,9 2974.1 .0 
975S.2 B703.1 7711.3 7157.0 6612.0 6040-5 5493.7 5331.» 4 545.3 4117.7 
3717.1 3341.0 3034.8 2703.8 2397.4 I2B5.7 
.303 .501 .503 .30 .502 .507 .514 .522 .533 .550 
.577 510 .652 ,713 .806 .000 
HACH = ,400, ALTITUDE •-• 5.000 . , THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS 
23503.6 25566,6 38747,6 1733S.2 15968.6 14452.1 129VB.9 11612.2 10348.0 
+ 7806.3 6555.4 56D2.3 4600.0 3606.1 3 
12093.9 10785.1 9534.6 E869.2 B193.8 71B5.5 6814.2 C793.4 5532.7 
+ 4606.3 1152.6 3736.0 3350.6 2970.9 1555.3 
.511 .512 .511 .512 .513 .525 .534 .514 
+ .590 .624 .667 .728 .824 .000 
MACH = .403, AURITUCFL » 0., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS 
27290.1 2 • 16 2 3 21769.7 20129.6 13542.7 16781.7 15071.1 11484.1 12016.1 
+ 936': 6 7723.2 -.•'.!•< . U 5341.5 41:17.4 .0 
14316.7 12767.4 11346.2 10499.3 9699.7 6tt1.3 8066.6 7737.6 6358.0 
* S«3 .0 4915.9 44552.7 3966.5 3517.0 1SSS.1 
.524 .522 ,521 .522 .52 3 .523 .535 .544 .555 
*• .602 .63- .630 .743 ,610 .000 
MACH = .300, ALTITUDE = 5000., THROSTS/FUWL FLOWS/SfCS/NOX RATIOS 
25221.8 22780.4 20475.9 18952.7 17 477,G 15S44.1 14241.2 12740.9 U389-B 
' 8*97.4 7263.9 6113.1 5047,7 7355.5 .0 
11717.0 1045,'.3 9303.6 6565.0 7869.3 7546.8 6460.9 5333.8 5253.4 
+ 4222.2 1772,6 3160.8 29/8.2 2533,2 1290.2 
,465 .459 ..154 ,552 .455 .451 .454 .458 .465 
+ .497 .339 .'J'JU . 5SO .605 .033 
MACH i .300, ALTITUDE = O., THRUSTS /FIIFf. FLOWS/RFr.S/KQJf RATIOS 
29925.9 23029.5 24254.9 22487.5 20736.6 1B799.2 1 6897.3 5 5:5.6.7 1 3195.4 
,.- 15082,2 8317.5 725-1.3 598B.4 4586.9 .0 
14181.3 32656.7 11260,3 10366.3 9521.9 5349.9 7819.7 7060.8 6353.3 
+ 511D.2 4566,C 4067.7 3604.6 3126.4 1531.6 
.474 .463 .461 .459 ,450 .463 .467 .475 
+• .507 .535 .561 .602 .682 .000 
MACH - .2'0, ALTITUDE = 5000., THRUSTS /FUEL FLOWS/SFOS/N'CX RATIOS 
27500.8 25077.4 25631.3 25972.5 19316.3 17157.4 15693.9 14033.7 12325.6 
•i- 9250.9 7BB7.4 6650.3 5293.1 3957.4 .0 
11509,8 10281.6 3152.3 8369.5 7636.9 6879.8 6166.8 :5 , 3 4917.3 
i JB74.7 5433.4 3014.4 5597.6 2210.9 1058.6 
.418 .411 ,404 .399 .395 ,393 .133 .393 .399 
+ .419 .434 .453 .431 .556 .000 
MACH = .200, ALTITUDE = O., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS 
32551.1 29999.5 271/6.4 25129.3 23145.3 23953.1 1E910.2 16821.0 14762.4 
' 11031.3 9450.6 796B.9 6342.1 4737.7 .0 
11080.4 12579.0 :, 97.4 1024O.1 935 3.4 8*17.1 7:>44.8 
+ 4710.5 4188.4 3687.5 3178.0 2717.1 12J5.2 
.427 .419 .412 .408 .434 .402 .401 
+ .428 .443 .463 .501 .567 .000 
67 53 51 6016.1 
.401 .438 
HACH = .100, ALTITUDE = 5500., 'ItfROSTS/FUEi 
30350.1 27786.1 23342.0 23463.4 21653.2 59521.5 1 
+ 10391.6 EES6.4 7409,2 5781.9 4429,6 .0 
11408.3 10192.8 9D75.9 5253.4 7455.5 6707.9 
* 3429.1 3178 B 2750.0 2330.0 1968.8 912.7 
.376 .357 .358 .335 .346 .342 
* .349 ,355 .371 ,403 .444 .000 
FLOWS/SFCS/NOX RATIOS 
?540.2 15716.2 1 • .2 
J971 . 3 .535 5293 . 3 -.-i? . 3 
.337 .340 
MACH - .503, ALTITUDE 0,, THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS 
361B9.0 33406.0 30467.6 28216.2 26029.1 23393.7 212011.0 IBB94.9 16574.5 
+ 12-153.1 10695.7 5907.8 6954.9 5325-6 .0 
14016,5 12523.1 11150.9 10146.4 920B.5 8241.5 7336.4 5511,4 5'54.0 
* 1159.1 39D5.5 3378.8 2862.7 24x3.3 1121.3 
.384 .375 .366 .350 .354 349 .346 .345 .347 
+ .357 .365 .379 .412 .454 .000 
FOLLOW 
5073.2 
5132.8 
.562 
FOLLOW 
10540.5 
6040 . 6 
.573 
FOLLOW 
9328 .3 
4713.4 
.480 
FOLLOW 
1 •••1.4 
FOLLOW 
10733.5 
4371 .7 
.407 
FOLLOW 
12867.2 
5348.4 
.416 
FOLLOW 
12025-3 
4130.5 
. 313 
FOLLOW 
11457.5 
5074 ,3 
.351 
MACH .000, \LT . -7J1SE 5305 . , RTFRUSTS/FUHL
 FLOWS/SFCS/NOX TlATIOS FOLLOW 
Nov 18 96 
15:09:03 C17-LONG-FLOPS-OUT 
33824.6 31141.5 28571,9 26468.4 24422.6 22105.5 19879.3 17675.0 15512.9 
11702.1 10019.1 8071.8 6-342.6 4892.9 .0 
11377.9 10166.9 9052.8 8186.1 7380.5 6545.0 5779.4 5083.5 4452.1 
3382.8 292B.O 2465.9 2065.1 1722.9 910.2 
.336 .326 .317 .309 .302 .296 .291 .288 .287 
.289 .292 .305 ,326 .352 .000 
MACH = .000, ALTITUDE = 0., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS 
40700.0 37471.4 34379.6 31848.5 29386.8 26598.8 23920.0 21267.7 18666.1 
14080.8 12055.6 9712.5 7631.9 5887.5 .0 
13995.6 12505.9 11135.6 10069.4 9078.6 8050.8 7109.0 6253.1 5476.4 
4161.0 3601.6 3033.2 2540.3 2118.0 1119.7 
.344 .334 .324 .316 .309 .303 .297 .294 .293 
,296 .299 .312 .333 .360 .000 
13534 .5 
3888 .9 
.287 
FOLLOW 
16285 .5 
4783 .6 
.294 
tt REVISED PROPULSION SYSTEM DATA 
BASELINE ENGINE THRUST THRSO 
BASELINE ENGINE WEIGHT WENG 
BASELINE INLET WEIGHT WINL 
BASELINE NOZZLE WEIGHT WN02 
BASELINE NACELLE LENGTH XNAC 
BASELINE NACELLE DIAMETER DNAC 
40700.0 LBF 
7100.0 LBF 
. 0 LBF 
,0 
12 .23 
LBF 
FT 
6.23 FT 
» NAMELIST SMISSIN 
PERFORMANCE CONTROLS AND FACTORS AND MISSION SEGMENT DEFINITION 
VALUE DIMENSIONS DESCRIPTION NAME 
ENDURANCE MISSION SWITCH INDR 
OVERALL FUEL FLOW FACTOR FACT 
CDO FACTOR FCDO 
CDI FACTOR FCDI 
SUBSONIC CD FACTOR FCDSOB 
SUPERSONIC CD FACTOR FCDSUP 
ENGINE SCALING SWITCH ISKAL 
OWE FACTOR OWFACT 
PRINT FLAG I FLAG 
DETAILED MISSION PRINT MSUMPT 
TEMPERATURE DEVIATION DTC 
CALC RAMP WT OR RANGE IRW 
RANGE TOLERANCE RTOL 
ATA TRAFFIC ALLOWANCE IATA 
WEIGHT INCREMENT DWT 
GROUND OPERATIONS AND TAKEOFF INPUT 
TAKEOFF TIME TAKOTM 
TAXI-OUT TIME TAXOT
APPROACH TIME APPRTM 
APPROACH FUEL FLOW FACTOR APPFFF 
TAXI-IN TIME TAXITM 
0 
oooo 
oooo 
oooo 
oooo 
oooo I 
oooo 
2 
1 
,0 
1 
0010 
o 
l. 
2.0 
15.0 
. 0 
2.00 
2.0 
MIN MIN MIN 
TAKEOFF POWER SETTING ITTFF 1 
TAXI FUEL FLOWS WILL BE FROM THE ENGINE DECK 
INPUT FOR 1 CLIMB SCHEDULES (1) 
MINIMUM CLIMB MACH NUMBER CLMMIN .3000 
MAXIMUM CLIMB MACH NUMBER CLMMAX .0000 
MINIMUM CLIMB ALTITUDE CLAMIN 0. 
FT 
MAXIMUM CLIMB ALTITUDE CLAMAX 0 . 
FT 
NUMBER OF CLIMB STEPS NINCL 31 
CLIMB OPTIMIZATION FACTOR FWF -1.0000 
FOLLOWING CRUISE SEGMENT NCRCL 1 
(2) 
.3000 
.0000 
0. 
31 
, 0010 
1 
(3) 
.3000 
.0000 
0. 
31 
.0010 
1 
(4J 
.3000 
.oooo 
0. 
0. 
31 
. 0010 
1 
DRAG COEFFICIENT INCREMENT 
NO. OF POWER SETTINGS 
STORE DRAG DURING CLIMB 
MAX CLIMB POWER SETTING 
FAA CLIMB ENFORCED 
FAA DESCENT ENFORCED 
MINIMUM CLIMB RATE SWITCH 
MINIMUM CLIMB RATE 
Q LIMIT IN CLIMB 
MAXIMUM RATE OF DESCENT 
INPUT FOR 1 CRUISE SCHEDULES 
(5) (6) 
CRUISE OPTION SWITCH 
1 1 
CRUISE OPT FUEL FACTOR 
1.000 1.000 
CRUISE OPT NOX FACTOR 
.000 .000 
MAXIMUM MACH NUMBER 
.0000 .0000 
MAXIMUM ALTITUDE 
-1. -1, FT 
DRAG COEFFICIENT INCREMENT 
,00000 .00000 
STORE DRAG DURING CRUISE 
0 0 
LONG RANGE CRUISE FACTOR 
1.000 1.000 
MINIMUM MACH NUMBER 
.0000 .0000 
MAXIMUM LIFT COEFFICIENT 
.0000 .0000 
ENGINE FEATHERING ALLOWED 
0 0 
ENGINE FRACTION REMAINING 
.5000 .5000 
CD INCREASE FOR FEATHERING 
.00000 .00000 
MINIMUM CRUISE ALTITUDE 
1000. 1000. FT 
INCREMENT IN CRUISE WT. 
RATE OF CLIMB CEILING 
INPUT FOR DESCENT SCHEDULE 
DESCENT OPTION SWITCH 
DESCENT LIFT COEFF. 
MINIMUM DESCENT MACH NO. 
MAXIMUM DESCENT MACH NO. 
MINIMUM DESCENT ALTITUDE 
MAXIMUM DESCENT ALTITUDE 
NUMBER OF DESCENT STEPS 
DRAG COEFFICIENT INCREMENT 
STORE DRAG DURING DESCENT 
RESERVE SEGMENT INPUT 
RESERVE CALC. OR CONST 
RESERVE FUEL 
FRACTION OF TRIP FUEL 
MISSED APPROACH TIME 
RANGE TO ALTERNATE AIRPORT 
RESERVE CLIMB SCHEDULE 
RESERVE CRUISE SCHEDULE 
START RESERVE MACH NUMBER 
END RESERVE MACH NUMBER 
START RESERVE ALTITUDE 
END RESERVE ALTITUDE 
CLDCE 
IPPCL 
ISTCL 
MAXCL 
IFAACL 
IFAADE 
NODIVE 
DIVLIM 
QLIM 
RDLIM 
IOC 
FPU EL 
FNOX 
CRMACH 
CRALT 
CRDCD 
ISTCR 
FLRCR 
CRMMIN 
CRCLMX 
IFEATH 
FEATHF 
CDFETH 
HPMIN 
DCWT 
RCIN 
IVS 
DECL 
DEMMIN 
DEMMAX 
DEAMIN 
DEAMAX 
NINDE 
DEDCD 
ISTDE 
IRS 
RESRFU 
RESTRP 
TIMMAP 
ALT RAN 
NCLRES 
NCRRES 
SREMCH 
EREMCH 
SREALT 
EREALT 
.ooooo 
1 
0 
1 
D 
0 
0 0. 
.0 
-99999.0 
(1) 
2 
1 .000 
.000 
.7500 
28000. 
.00000 
0 
1.000 
.3000 
.0000 
0 
.5000 
.ooooo 
1000 . 
1.0 
100.0 
1 
.8000 
.3000 
,0000 
0. 
0 . 
31 
. ooooo 
0 
.00000 
1 
0 
FT/MIN 
PSF 
FT/MIN 
(2) 
1 
1 .000 
.ooo 
,0000 
-1. 
.ooooo 0 
1.000 
.0000 
.0000 
c 
.5000 
.ooooo 
1000. 
LBF 
FT/MIN 
FT 
FT 
. 000 LBM 
. ooo 
2.0 MIN 
500.0 N MI 
1 
1 
.3000 
.3000 
0. FT 
0. FT 
15:1)9:03 C17-LONG-FLOPS-OUT 
RE5EHVE HOLDING TINS HCLDTH .0 •• ! •.0031O -.00281 - .002 62 •.D0243 -.00237 
0D223 
-.00225 -.00223 
HOLD CRUISE SCHEDULE NCRHQL . -.00221 -.00219 --00217 
HOLD POSITION SWITCH IHQPOS j. 20D0D. --Q0272 -,00246 -.00230 -.00218 -.00208 -.00199 -.00197 -.OC -6 
CRUISE ONLY SWITCH ICRON 0 * - .00194 -.00192 -.00190 
2ND RES HOLD TIME OR FRAC THOLD 000 MIN 24000. -.00231 -.00209 -.00195 - . 00185 -.00176 -.00169 -.00167 -.00166 
THOLD CRUISE SCHEDULE NORTH 1 + -.00164 -.00163 ;1 
3 0000. -.00187 -.00169 -.00108 -.00149 -.00142 -.00137 -.00135 -.00134 4 
-.00133 -.00133 -.00130 
3 500D. -.00140 -.00126 -.00117 -.00111 -.00106 -. ooioi -.00000 -.00100 
IS.?ION SEQ'Jkr C£ DSFjtNJTION 4 -.00< • -.00098 •.00097 
4DP00. -.00074 - .00067 -.00062 -.00059 -.00056 -.00054 -.00053 .000:3 
START MACH HVMBER = .3000 ALTITUDE = 0 . rl 4--.00052 -.00052 -.00051 
C1.1N USE CI.IMH SCHEDULE 1 45000. .OOOOO . OOOOO .00000 .000DO .00000 .ooooo .0D0O0 .OOOOO 
CRUISE USE CRUISE SCHEDULE 1 END CRUISE DISTANCE = 4100 0 N MI + .00000 .OOOOO .00 • 
RELSAME PAYLOAD WEIGHT = 30000.0 LI* 50000. .00079 .00071 .00066 ,00062 ,00059 ,00057 .00056 .00056 
REFUEL FUEL ADEEa • -2 000.0 LB TrHK REOVt RED i-lflS, 0 MIN + .DOOSS .00054 .00054 
CRUISE USE CRUISE SCHEDULE 1 END CRUISE DISTANCE 500 0 N MI 55000. .00162 00146 .00134 .00128 .00122 .00116 .00115 .00114 
DESCENT 4 .00113 .00112 .00111 
BUG MACH N'.JMBSR = .3000 ALTITUI04 0 . FT 6 .00251 .00226 .00209 .00197 ,001S8 .00180 .D0179 ,00176 
+ . 00175 .00173 .00171 
•TITLE. BEGIN OUTPUT OF RESULTS 
C17 Long Mission 
FINAL ANALYSIS 
# AERODYNAMIC DATA 
DRAG POLARS 
MACH NUMBER 
.75 
COMPONENT 
CDF 
WING 
42 .00533 
HORIZONTAL TAIL 
65 .00156 
VERTICAL TAJL 
48 .OC i 
FUSELAGE 
83 .00477 
NACELLE 
67 .00040 
NACELLE 
67 .Q0D4O 
NACELLE 
67 .00040 
NACELLE 
67 00040 
MISI tL UJEOUS 
ALTITUDE 
45000. FT 
REFERENCE AREA 
00'o.oo 
TECHNOLOGY LEVEL 
1 . 20 
SQ FT 
5819.15 
I0j't7. 80 
806 . 95 
8036.68 
213.34 
213.34 
213.34 
213.34 
FT 
23 . 25 
13 . 00 
19 . 88 
159.10 
12 .23 
12 .23 
12.23 
12 . 23 
RATIO 
. 1210 
. 0 b 4 0 
.1100 
7.2220 
1 . 9631 
1 . 9631 
1.9631 
1.9631 
FACTOR 
1 . 440 
1 . 3 05 
1.398 
1 .233 
2 ,663 
2 . 663 
2 . 663 
2.663 
MILLIONS 
26.3 
14.7 
22 .5 
179 .9 
13.8 
13 . 8 
13 . 8 
13 . 8 
.002 
.002 
.001 
, 002 
. 002 
. 0O2 
, 002 
MACH 
.500 
.200 
03416 
.300 
03286 
.400 
03197 
.500 
03127 
.600 
03104 
.700 
03113 
.725 
03327 
.750 
03174 
.775 
03399 
.800 
03797 
.825 
05902 
.050 
.550 
.01982 
.03832 
.01852 
.03702 
.01763 
.03613 
.01693 
.03543 
.01670 
.03520 
.01692 
.03531 
.01706 
.03544 
.01742 
.03619 
.01816 
03882 
.01980 
.04331 
.03497 
.06529 
.100 
.600 
.01934 
04314 
.01854 
04194 
.01765 
04095 
.01696 
04026 
.01673 
04003 
. u 6b6 
04D12 
.01697 
04022 
.01724 
U409B 
.01732 
04359 
.01925 
04903 
.03355 
07117 
.150 
.650 
,02027 
.04642 
.01397 
04713 
.01B08 
04624 
.01739 
04554 
. 01016 
04531 
.0,1723 
04540 
.01136 
04547 
.0:75 • 
04 . .1 
.01911 
04 320 
.01947 
05470 
.03337 
07735 
.200 
.7 00 
. 02H1 
05527 
.01981 
S5397 
.01892 
95303 
.01H22 
042J8 
.01799 
05215 
.01811 
05223 
.01822 
05228 
.01847 
05261 
• 01.902 
0554 0 
.00 04 6 
06092 
.03447 
0836E 
+ .00034 .200 
.300 
.01906 
. Ii"" 6 
.ooooo 
.ooooo 
1 .051 
. 996 
TOTAL 1723.0 94 .003 .400 .01667 .' )0 D .919 4 
.01484 .500 
.600 
.01618 
,01559 
.ooooo 
.00035 
. ;:.-: ;. 
.745 
CHANGE IN DRAG COEFFICIENT FROM CRUISE ALTITUDE .700 .01508 .00097 .640 
ALTITUUE MAO! NUMBER .740 . 0 . .00119 .603 
.200 .300 .400 .: )0 . 600 .700 .72 5 .750 . 7 5 0 ,01494 .00155 .562 
• . 775 .825 .775 .01472 .1
 )217 
. 510 
0. . 00409 .00372 -,00347 -.00329 -.00315 -.00302 - .00299 -.00296 .800 .D1461 
. i -13- . . t i
 i 4 
-.00294 -. 0020 1 - 002B8 .825 .01449 .01755 ,40-3 
5DOO. .00378 - .003J4 -.00321 -.00304 -.00290 -.00279 - .0O276 -.0O274 4 
- 0007] 00269 - 002 66 CL COI 
J00DO. 00345 - .00313 -.00292 -.00277 -.00265 -.00254 -.00252 -,00240 4 
-.002 47 002 45 - 00243 .05.0 .00031 
DESIGN MACH NUMER 
MACH 
,771, DESIGN CL 
CDF 
0 000. FT 
.250 
. 750 
.02235 
. 06357 
.02105 
.06228 
.02016 
. 06139 
.01947 
. 06069 
,00923 
. 06046 
.015 -2 
.06054 
.01951 
.06053 
.019B7 
. 06063 
.02056 
.06255 
. 02222 
. 06746 
.03683 
.09009 
.458 
CDC 
. 300 
. 02390 
. 02261 
. 02172 
.02102 
,02030 
.02101 
. 02116 
. 02152 
. 02228 
.02417 
.03990 
.350 
.02577 
.02447 
.02359 
. 02290 
. 02268 
.02291 
.02307 
. 02341 
. 024JO 
. 02627 
.04368 
. 400 
.02781 
.02651 
.02563 
.02496 
.02477 
.02499 
.02517 
.02555 
.02645 
.02926 
.04859 
BUFFET CL 
.450 
.03068 
.02939 
.02-350 
.027B1 
.02760 
.02772 
.02785 
.02828 
.02902 
.03346 
.05348 
Nov 18 96 1V7H 
]5:W:m C17-LONG-FLOPS-OUT W*M 
.100 .00044 324000. 28000. 30496. 21200. 14734. . 6950 .7500 445 9 .0302 
. 150 .00099 + 6 1295.5 .3143 15 28 4 0 .00 
.200 ,00177 342000. 28000. 30496. 21879. 15070. , 6888 ,7500 445 9 .0295 
.250 .00276 + 9 1137.6 .3318 15 63 4 .0 ,00 
.300 .00398 360000. 28000, 30496. 22590. 15428. .6830 .7 500 445 9 .0289 
.350 .00542 4 0 991,6 .3492 15 94 4 0 .00 
.400 .00707 378000. 28000. 30496. 23328, 15803. . 6774 .7500 445 9 ,0282 
.450 .00895 + 1 856.2 .3667 16 20 4 0 ,00 
.500 .01105 396000. 28000. 30496. 24096. 16193. .6720 .7500 445 9 .0275 
.550 .01337 4 3 729.8 .3841 16 43 4 0 .00 
.600 .01592 414000, 28OO0. 30496, 24899. 16610. . 6671 . 7500 445 9 ,0268 
, 650 .01868 + 4 610. 4 .4016 16 63 4 0 .00 
.700 .02166 432000. 28000. 30496. 25820. 17087. . 6618 .7500 445 9 .0260 
.750 .02487 4 9 488.7 
450000. 
.4191 
28000. 
16 73 
30496. 
4 0 
26818. 
.00 
17612. .6567 ,7500 445 9 .0253 
PRESSURE DRAG COEFFICIENTS.. CDP 4 2 369,1 .4365 16 78 a 0 .00 
MACH CL 468000. 28000. 30496. 27896. 18186. .6519 .7500 445 9 .0245 
. 050 . 10C .150 .200 ,2 50 .300 .350 .400 .450 4 2 250.8 .4540 16 78 4 0 ,00 
+ . 500 .550 . 600 ,650 .700 .750 486000. 28000. 30496. 29077. 18814, . 6470 .7500 445 9 .0237 
. 20C ,00065 .00034 .00021 .00028 . 00053 .00087 00130 ,00168 .00267 4 0 131.8 . 4715 16 71 4 0 ,00 
+ 00404 .00588 00816 01069 01454 01965 504000. 27439, 31282. 30163. 19530. . 6474 . 75O0 44 6 9 .0228 
.300 .00065 .00034 .00021 .00023 .00053 .00087 00130 .00168 .00267 4 8 100. 0 . 4769 16 71 4 0 .00 
+ 00404 .00588 00816 01069 01454 01965 522000. 26677, 32349. 31200. 20264. .6495 ,7500 443 4 .0221 
.400 .00065 .00034 .00021 ,00028 .00053 .00087 00130 .00169 .00267 . 4 3 100.0 .4775 16 73 4 0 .00 
+ 00404 .00583 00816 01069 01454 01965 540000. 25919. 33410. 32225. 20993. .6515 .7500 449 8 .0214 
.500 .00065 .00034 .00021 .00028 .00053 .00087 00131 .00171 .00268 . 4 3 100.0 .4778 16 76 4 0 .00 
+ 00404 .00588 00816 01069 01454 01965 558000. 25166. 34465. 33243. 21717. .6533 .7500 451 2 .0207 
.600 .00064 .00034 .00021 .00028 .00052 .00088 00131 .00175 .00270 . + 8 100.0 .4777 16 79 4 0 .00 
t 00404 
,00588 00816 01069 01454 01965 576000. 24497. 35540. 34283. 22472, . 6555 .7500 452 5 .0201 
.700 .00076 .00037 .00022 .00030 .00061 .00099 00145 .00187 ,00273 . + 3 100. 0 .4790 16 80 4 0 ,00 
4- 00404 
.00589 00816 01O68 01453 01963 534000. 23854, 36618. 35325. 23233. . 6577 ,7500 453 7 ,0195 
.725 .00080 .00038 .00021 ,00030 .00064 .00104 00150 .00195 .00275 4 3 100.0 .4804 16 82 4 0 .00 
* 7 .00592 00816 01O64 01447 01957 612000. 23213. 37691, 36363, 23990. .6597 .7500 454 8 ,0189 
.75C .00092 .00041 .00021 .00032 .00073 .00116 00162 ,00209 ,00295 + 6 100. 0 ,4815 16 83 4 0 .00 
* 00430 .00644 00869 01097 01456 01938 630000. 22576. 38759. 37395. 24743. .6617 .7500 456 0 .0184 
.775 .00116 .00048 .00022 . 00036 .00091 ,00141 00139 .00249 ,00398 4 3 100.0 .4824 16 85 4 0 . 00 
+ 00605 .00855 01108 01363 01689 02079 648000. 21942. 39822. 38423. 25493. . 6635 .7500 457 2 .0179 
. 800 .00151 .00062 .00029 .00050 .00127 ,00201 00267 .00400 .00632 . 4 3 100 ,0 .4329 16 87 4 0 .00 
* 00873 .01175 01493 01783 02107 02441 666000. 21312. 40879, 39444. 26239. . 6652 .7500 458 4 .0174 
. 825 .00282 .00106 .00033 .00066 .00202 .00387 00622 .00947 .01248 . 4 7 100 .0 .4833 16 88 4 0 .00 
+ 01592 .01987 .02321 .02663 .02997 .03318 
U CRUISE OPTIMIZATION RESULTS SUMMARY DATA FOR CRUISE SCHEDULE 1 
WEIGHT ALTITUDE THRUST FUEL SFC MACH 4 
C RATE OF CL L/D ENGINES NOX 
AVAILABLE REQUIRED FLOW NUMBER 
4 CLIMB OPERATING RATE 198000. 2S0OO. 30496. 17343 12848. .7408 ,7500 4 
0 2999.4 .1921 11 42 4 .0 .00 
216000. 28000. 30496, 17757 13050. .7349 .7500 4 
7 2662 . 9 ,2095 12 16 4.0 . 00 
234000. 28000. 30496. 18237 13283. .7284 .7500 
4 7 2365 . 5 .2270 12 83 4.0 .00 252000. 28000, 30496. 18784 13549. .7213 .7500 4 1 2098.6 .2445 13 42 4 .0 .00 
270000. 2 8000, 30496. 19353 13826. .7144 .7500 4 
5 1863 .5 .2619 13 95 4 .0 .00 
2B8000. 28000. 30496. 19938 14111. ,7078 ,7500 4 
0 1655 .3 .2794 14 44 4 .0 .00 
306000. 28000. 30496. 20553 14415, ,7013 .7500 4 
3 1467.2 .2968 14 89 4.0 .00 
CRUISE SCHEDULE RANGE AND TIME SUMMARY 
WEIGHT RANGE -1- TIME 
(POUNDS) IN.MI.) <HR) 
666000. 0 . 00 
657000. 158 7 .35 
VELOCITY SPECIFI 648000. 318 6 ,70 
639000. 481 1 1.05 
RANGE 630000. 645 8 1 .41 
621000. 812 9 1 .78 
612000. 982 3 2 .15 
445 9 .0347 603000. 1154 2 2 .53 
594000. 1328 6 2.91 
445 9 , 0341 585000, 1505 7 3.30 
576000. 1685 5 3.70 
445 9 . 0335 567000. 1868 1 4.11 
558000. 2053 6 4 . 52 
445 9 .0329 549000, 2242 1 4.93 
540000. 2433 4 5.36 
445 9 .0322 531000. 2627 8 5.79 
522000. 2825 3 6 .23 
445 9 .0316 513000. 3026 1 6.68 
504000. 3230 3 7 .14 
445 9 . 0309 495000, 3438. 1 7.60 
486000. 3649 5 8 . 08 
C17-LONG-FLOPS-OUT 
477000, 3864 6 8 56 396000, 0. 69 0 6149 7 331 3 11806 0 99 6 1727 0 
458000. 4085 4 9 05 + 21549. 374451 .7500 28000. 44S 9 
1159000 . 4305 8 9 55 414000. 0, 74 2 6581 2 326 2 11899 5 99 6 1734 7 
450000. 4531 8 10 05 + 22081. 391919 .7500 2 8000. 445 9 
441000. 4761 3 10 57 432000. 0 . 79 8 7044 2 320 5 11988 6 99 6 1741 5 
432000. 4994 4 11 09 22640. 409360 .7500 28000. 445 9 
423000. 5230 9 11 62 450000. 0. B6 1 7545 8 314 3 12084 7 99 6 1748 4 
414000. 5470 8 12 16 + 23245. 426755 .7500 28000, 445 9 
405000. 5713 9 12 71 468000. 0, 93 3 8099 5 307 2 12166 7 99 6 1755 1 
396000. 5960 1 13 26 4 23887. 444113 .7500 28000. 445 9 
387000. 6209 5 13 82 486000. 0 . 101 6 8722 5 299 0 12219 3 99 5 1760 4 
378000. 6461 8 14 38 + 24568. 461432 ,7500 28000. 445 9 
369000. 6717 3 14 96 504000. 0. 108 1 9274 7 292 7 12362 9 99 2 1765 0 
360000. 6975 8 15 54 4 2S269. 473731 .7500 27439. 446 9 
351000. 7237 4 16 12 522000. 0. 110 4 9624 5 291 4 12735 7 98 2 1761 9 
342000, 7502 1 16 72 4 25988. 496012 .7500 26677. 448 4 
333000. 7769 9 17 32 540000, 0. 110 5 9871 7 293 1 13238 1 96 4 1750 a 
324000. 8040 7 17 92 4 26727. 513273 .7500 25919. 449 8 
315000. 8314 6 18 54 558000. 0. 110 3 10104 8 295 2 13764 5 94 4 1737 4 
306000, B591 4 19 16 + 27473, 530527 .7500 25166. 451 2 
297000. 8871 3 19 79 576000. 0. 110 4 10356 0 297 1 14232 6 92 5 1723 4 
288000. 9154 1 20 42 + 2B228. 547772 ,7500 24497. 452 5 
279000, 9440 0 21 06 594000. 0 . 110 9 10637 3 298 6 14793 6 90 6 1709 9 
270000. 9728 7 21 71 + 29007. 564993 .7500 23854. 453 7 
261000. 10020 4 22 36 612000. 0. 111 7 10950 3 299 5 15280 8 88 S 1697 8 
252000. 10315 1 23 03 + 29795. 582205 .7500 23213 . 454 8 
243000. 10612 7 23 69 630000. 0. 112 4 11274 1 300 4 15771 7 87 1 1684 9 
234000. 10913 3 24 37 4 30597 . 599403 .7500 22576. 456 0 
225000. 11216 8 25 05 64BOOO. 0. 113 1 11618 8 301 4 16263 3 85 5 1671 8 
216000. 11522 9 25 73 + 31420. 616530 ,7500 21942. 457 2 
207000. 11831 6 26 43 666000, 0. 114 1 12016 9 302 1 16738 8 83 8 1658 1 
198000. 12142 7 27 12 + 32280. 633720 .7500 21312. 458 4 
# RESERVE SUMMARY 
MISSED APPROACH FUEL 1866. LB, 
CLIMB CLIMB CRUISE 
DIST FUEL DIST 
START HOLDING 
RESERVE END 
RESERVE FUEL 
FUEL RESERVE MACH 
WEIGHT 
WEIGHT NUMBER ALTITUDE VELOCITY 
198000. 0. 27.6 2562.0 378.0 
16859. 181141. .7500 28000. 445.9 
216000. 0. 30.7 2829.3 374.3 
17077. 198923. .7500 28000. 445.9 
234000. 0. 33,9 3105.1 370.5 
17442. 216558. .7500 28000. 445.9 
252000. 0. 37.2 3390.3 366.5 
17839. 234161. .7500 28000. 445.9 
270000. 0. 40.6 3686.7 362.3 
18258. 251742. .7500 28000. 445.9 
288000. 0. 44.2 3993.7 358.0 
18685. 269315. .7500 28000. 445.9 
306000. 0. 47.8 4313.7 353.8 
19126. 286874. .7500 28000. 445.9 
324000. 0. 51.6 4645.9 349.6 
19582. 304418. .7500 28000. 445.9 
342000, 0. 55.6 4993.7 345.3 
20048. 321952. .7500 28000. 445.9 
360000. 0. 59.8 5359.5 340.8 
20530. 339470. .7500 28000. 445.9 
378000. 0. 64.3 5744.1 336.2 
21033. 356967. .7500 28000. 445.9 
CRUISE DESCENT 
FUEL DIST 
10934.2 
10860.4 
10926.4 
11010.1 
11099.4 
11189.9 
11287.2 
11392.5 
11495.4 
11597.6 
11704.3 
94 .4 
95 .0 
95. 6 
96. 3 
97 . 1 
97 .8 
98 .4 
98.8 
99.1 
99 .4 
39 .5 
DESCENT 
FUEL 
1496.8 
1520.9 
1544.9 
1572.7 
1605.6 
1635.5 
1658.9 
1677.6 
1693 .1 
1707.3 
1718.0 
ITERATION 1 — 
ITERATION 2 -¬ 
ITERATION 3 -¬ 
ITERATION 4 — 
ITERATION 5 --
RANGE 
RANGE 
RANGE 
RANGE 
RANGE 
9306.033 
5378 .623 
4419.514 
4604.663 
4599.999 
tt OUTPUT FROM THE WEIGHTS MODULE 
DESCRIPTION 
CALCULATED WING AREA 
CALCULATED ASPECT RATIO 
WING BENDING FACTOR 
ENGINE INERTIA RELIEF FACTOR 
WING WEIGHT BREAKDOWN 
TERM 1 
TERM 2 
TERM 3 
WING SPAN 
WING GLOVE AREA 
HORIZONTAL TAIL AREA 
MODIFIED VOLUME COEFFICIENT 
VERTICAL TAIL AREA 
MODIFIED VOLUME COEFFICIENT 
FOR GROSS WEIGHT = 
FOR GROSS WEIGHT = 
FOR GROSS WEIGHT = 
FOR GROSS WEIGHT = 
FOR GROSS WEIGHT = 
VALUE DIMENSIONS 
3846.0 SQ FT 
7 .28618 
9.2021 
.914368 
11915.5 LB 
17833.9 LB 
7829.7 LB 
167.40 FT 
-92.05 SQ FT 
845.00 SQ FT 
1.539989 
395.07 SQ FT 
.100000 
650000.00 
453781.57 
414880.53 
422200.96 
422016.58 
Nov 18 96 
15:09:03 C17-LONG-FLOPS-OUT 
NACELLE LENGTH 
NACELLE DIAMETER 
LENGTH OF MAIN GEAR 
LENGTH OF NOSE GEAR 
MAXIMUM LANDING WEIGHT 
WING FUEL CAPACITY 
FUSELAGE FUEL CAPACITY 
AUXILIARY TANK CAPACITY 
TOTAL FUEL CAPACITY 
1 MASS AND BALANCE SUMMARY 
T LREF HORI CG-INCHES 
WING 
.0 .0 
HORIZONTAL TAIL 
.0 .0 
VERTICAL TAIL 
.0 .0 
VERTICAL FIN 
.0 .0 
FUSELAGE 
.0 .0 
LANDING GEAR 
.0 .0 
NACELLE (AIR INDUCTION! 
,0 .0 
STRUCTURE TOTAL 
.0) ( .0) 
ENGINES 
.0 .0 
THRUST REVERSERS 
.0 73.4 
MISCELLANEOUS SYSTEMS 
.0 .0 
FUEL SYSTEM-TANKS AND PLUMBING 
.0 .0 
PROPULSION TOTAL 
.0) ( .0) 
SURFACE CONTROLS 
.0 .0 
AUXILIARY POWER 
.0 .0 
INSTRUMENTS 
.0 .0 
HYDRAULICS 
.0 .0 
ELECTRICAL 
.0 .0 
AVIONICS 
.0 .0 
FURNISHINGS AND EQUIPMENT 
.0 .0 
AIR CONDITIONING 
.0 ,0 
ANTI-ICING 
.0 .0 
SYSTEMS AND EQUIPMENT TOTAL 
.0) ( .0) 
WEIGHT EMPTY 
.0 .0 
CREW AND BAGGAGE-FLIGHT, 3 
.0 .0 
12.23 FT 
6.23 FT 
41.91 IN 
29.33 IN 
276420.9 LB 
182720.0 LB 
.0 LB 
.0 LB 
182720.0 LB 
PERCENT WREF 
8.90 
.71 
. 30 
.23 
15 .21 
2.26 
.82 
( 28.43) 
6 .73 
.00 
.23 
. 47 
7 . 43) 
1.03 
.15 
.22 
.60 
.75 
.62 
3 .35 
.53 
.07 
7.31) 
43 .17 
( 
( 
POUNDS 
37579. 
2987 . 
1256. 
981 . 
64181. 
9523 . 
3478 . 
( 119985.) 
28400. 
0. 
959 . 
1984 , 
( 31343.) 
4344 . 
616 . 
913. 
2541. 
3155 . 
2599 , 
14129. 
2248 . 
311 . 
I 30856.) 
182185. 
UNUSABLE FUEL 
.0 
ENGINE OIL 
.0 
PASSENGER SERVICE 
.0 
CARGO CONTAINERS 
. 0 
OPERATING WEIGHT 
PASSENGERS, 
.0 .0 
PASSENGER BAGGAGE 
.0 .0 
CARGO 
.0 .0 
ZERO FUEL WEIGHT 
.0 .0 
MISSION FUEL 
.0 .0 
RAMP. (GROSS) WEIGHT 
,0 .0 
B NONCRUISE SEGMENT RESULTS 
CLIMB PROFILE DATA FOR SEGMENT 1 
- - - CUMULATIVE - - -
. 00 
,23 
.08 
.00 
2.20 
4 5.84 
,00 
. 00 
11.85 
57 .69 
0 . 
983 . 
325. 
0. 
9275 . 
193443. 
0. 
0 . 
50000. 
243443. 
178573. 
422017. 
INCREMENTAL- -
.16 
WEIGHT ENERGY ALT MACH VEL RCI PC TIME DIST FUEL Q 
+ TIME DIST FUEL CL L/D THRUST /TMAX 
419031 1743 . 0 ,300 198. 4 3937 . 1 .00 0 0 133 3 
+ .00 0 .0 827 11.14 119703 1.000 
418702 3403 . 0 .419 277,3 5657. 1 .35 1 4 329 0 2 60 2 
+ .35 1 4 329 .0 423 18.18 107400 1. 000 
418429 5063 . 0 , 511 338.2 6027. 1 .28 1 5 273 2 387 2 
+ .63 2 8 602 .2 284 16 .55 98916 1. 000 
418163 6722. 1287 ,532 350.4 5877 . 1 .28 1 6 266 1 400 2 
+ .91 4 4 868 ,4 275 16 .27 94961 1 .000 
417397 8382. 2787 . 543 355 .5 5698. 1 .29 1 7 265 9 394 0 
+ 1.20 6 1 1134 .3 279 16.33 91733 1 .000 
417631 10042, 4264 .554 361.3 5541. 1 .30 1 7 265 6 3 89 3 
+ 1 . 49 7 8 1399 .8 282 16 .36 88787 1.000 
417365 11701. 5394 .581 377 . 4 5429 . 1 .30 1 s 265 7 410 7 
* 1.79 9 7 1665 , 6 2 67 15 .88 85568 1 . 000 
417098 13361. 6938 .530 3 80.9 5080 . 1 .32 2 0 267 7 399 0 
+ 2.11 11 7 1933 .3 275 16.03 80956 1.000 
416826 15020. 8276 . 608 390.3 4801 . 1 .34 2 1 271 3 402 C 
+ 2.45 13 8 2204 . 6 273 15.88 76880 1.000 
416551 16630. 9616 . 625 399.5 4557 . 1 .35 2 3 275 0 403 8 
+ 2 . 80 16 1 2479 . 6 271 15 .75 73384 1.000 
416272 18340. 10816 .648 412 .3 43 65 . 1 .37 2 5 279 1 414 2 
3.17 18 6 2758 ,7 264 15 .43 70506 1.000 
415988 19999. 12325 .658 416.4 4039 , 1 .40 2 7 284 6 402 7 
+ 3 .57 21 4 3043 . 3 272 15.55 66600 1.000 
415696 216S9. 13817 . 669 420.9 3707 . 1 .43 3 0 291 8 392 3 
+ 4.00 24 3 3335 . 1 279 15.64 62731 1.000 
415395 23319, 15420 . 675 422 .4 3351, 1 .47 3 3 300 5 375 0 
15:09*03 C17-LONG-FLOPS-OUT 
4.47 
415084 
4.97 
414762 
5.52 
414425 
6.12 
414070 
6.81 
413694 
7 . 59 
413288 
8 .50 
412843 
9 .57 
412345 
10.86 
412278 
11 . 04 
27 . 
31 . 
35 . 
50. 
57 . 
6 3635 
24978 
3 3946 
26638 
3 4269 
28298 
39.8 4606 
29957. 
44.8 4960 
31617 
6 5337 
33277 
4 5742 
34936. 
65.3 6188 
36596 
74.9 6686 
36801 
76.3 6752 
6 
16444 
.6 
17881 
3 
19497 
2 
212S3 
7 
22820 
.1 
24475 
9 
26135 
1 
27795 
2 
28000 
7 
291 
279 
285 
2 99 
320 
334 
354 
375 
397 
400 
15 .88 
705 
15.37 
718 
15.3 3 
724 
15.63 
725 
16 .01 
734 
16 .12 
739 
16.31 
744 
16 .47 
749 
16 . 60 
750 
16.61 
58697 
439 .1 
56680 
444 .8 
53727 
445 . 9 
50191 
443 .4 
46676 
445.8 
43833 
445 .9 
40746 
445 . S 
37996 
445,9 
35401 
445.9 
35080 
1,000 
3179 , 
1.00C 
2908. 
1 .000 
2580. 
1.000 
2258 . 
1.000 
1982 . 
1.000 
16S2 . 
1 .000 
1414 . 
1.000 
1157 . 
1.000 
1124 . 
1.000 
DESCENT PROFILE DATA FOR SEGMENT 6 
- - - CUMULATIVE - - -
HEIGHT ENERGY ALT MACH 
TIME DIST FUEL CL L/D 
VEL RCI PC 
THRUST /TMAX 
210453 . 
.00 
210600. 
-1 .46 
210738. 
-2 .91 
210866. 
-4 .34 
210986. 
-5.73 
211098 . 
-7.09 
211201 . 
-8.41 
211296. 
-9.71 
211384. 
10.97 
211464. 
12 .20 
211537. 
13 .40 
211602. 
14.58 
211660. 
15,72 
211711. 
16.84 
211755. 
17 .93 
211792. 
18.99 
211823. 
20.03 
211848. 
21.02 
211875. 
21 .99 
211912. 
22 .86 
1743 , 
.0 
0 
0 
1718 
0 
3336 
19 
33 
37 
51 
60 
65 
4930 
i 
6508 
3 
8082 
69 . 8 
78 
87 
3403 . 
8 -147 
5063 . 
5 -284 
6722 . 
2 -413 
8382 , 
0 -533 
10042. 
7 -644.8 
11701. 9651 
4 -748.1 
13361. 11216 
0 -843.4 
15020. 12776 
7 -931.0 
16680. 14332 
4 -1011.0 
18340. 15883 
1 -1083.6 
19999. 17429 
7 -1149.1 
21659. 19003 
3 -1207.5 
23319. 20632 
9 -1258.3 
24978. 22235 
4 -1302.1 
26638. 23850 
1339 . 3 
28298. 25447 
2 -1370.5 
29957. 27147 
3 -1395.1 
31617. 2800C 
7 -1421.7 
33277, 28000 
2 -1458.9 
.300 198 
415 17.61 
.297 195 
453 17.44 
.302 197 
464 17.35 
.309 201 
469 17.29 
,318 205 
471 17.27 
.327 210 
473 17.24 
.337 215 
475 17,21 
.346 220 
477 17.17 
.356 225 
479 17.14 
.367 230 
482 17.10 
.377 235 
485 17.06 
.388 240 
488 17.02 
.397 244 
497 16.90 
.402 246 
520 16.63 
.409 248 
538 16.37 
.415 250 
560 16.04 
.422 253 
579 15.74 
.422 252 
624 15.04 
.481 285 
500 16.81 
.581 345 
343 16.47 
.4 -1141. 0 
0. .000 
.1 -1133. 0 
0. .000 
.5 -1153. 0 
0. .000 
.2 -1178. 0 
0. .000 
.7 -1207. 0 
0. .000 
,4 -1236. 0 
0. .000 
.2 -1267. 0 
0. .000 
.1 -1298. 0 
0. .000 
.2 -1330. 0 
0. .000 
.3 -1364. 0 
0. .000 
.6 -1398. 0 
0. .000 
,9 -1434. 0 
0. .000 
.9 -1467. 0 
0. .000 
.4 -1500. 0 
0. .000 
.9 -1540. 0 
0. .000 
.9 -1584. 0 
0. .000 
.7 -1633. 0 
0. .000 
.0 -1697. 0 
0. .000 
.8 -1722. 0 
0. .000 
.2 -2123. 0 
0. .000 
, 51 
.55 
. 60 
. 69 
.78 
.91 
1.07 
3 .6 
4 .0 
4.5 
311.0 391.8 
322.7 383.4 
5.1 354.5 
5.8 376.4 
336.9 365.0 
340.1 
325.7 
6.7 
8.0 
1.29 9.6 
.13 1.3 
405,8 307.6 
445.2 290.0 
498.1 273.3 
66.5 271.3 
- - INCREMENTAL- -
TIME DIST FUEL 
.00 ,0 
-1.46 4.8 
-1.45 4.7 
-1.42 4.7 
-1.39 4,7 
-1.36 4.7 
-1.33 4.7 
-1.29 4.7 
-1.26 4.7 
-1.23 4.7 
-1.20 4.7 
-1.17 4.6 
-1.14 4.6 
-1.12 4.6 
-1.09 4.5 
-1.06 4.4 
-1.03 4,3 
•1.00 4,2 
-.97 4.3 
.86 4.5 
.0 
-147.0 
-137.8 
-128 . 6 
-119.9 
-111.5 
-103.3 
-95,3 
-87 . 6 
-80 .0 
-72.7 
-65.5 
-58 .3 
-50 . 9 
-43 .7 
-37 . 2 
-31,2 
-24.5 
-26.7 
-37.1 
133 .3 
122 .5 
119.6 
118.3 
117 . 9 
117 . 5 
117 .1 
116.6 
116,1 
115 . 5 
114 .9 
114 .2 
112 .0 
107 . 2 
103 .6 
99 . 6 
96.2 
89,3 
111,5 
162 . 6 
211951. 34936. 28000. .666 395.8 -2782. 0 -.68 
* 23.53 91.4 -1497,8 .261 14.41 0. .000 
211985. 36596. 28000. .741 440.6 -3632. 0 -.52 
* 24.05 95.0 -1532.6 .211 12.29 0. .000 
211989. 36801. 28000. .750 445.9 -3761. 0 -.06 
+ 24.11 95.4 -1536.6 .206 12.00 0. .000 
4.2 
3 .6 
.4 
-39 .0 
-34.7 
-4.0 
213 .8 
265.0 
271.3 
ITERATION RANGE = 4600.000 FOR GROSS WEIGHT 422016,62 
It SIZING AND PERFORMANCE RESULTS 
CONFIGURATION DATA AFTER RESIZING (IF ANY) 
OPERATING WEIGHT EMPTY 
PAYLOAD 
MAXIMUM FUEL 
GROSS WEIGHT 
REFERENCE WING AREA 
WING LOADING 
THRUST PER ENGINE 
ENGINE SCALE FACTOR 
THRUST-WEIGHT RATIO 
193443.3 LB 
50000.0 LB 
173573.4 LB 
422016,6 LB 
3800.00 SQ FT 
111.06 LB/SQ FT 
40700.0 LE 
1 . 0000 
.3858 
INITIAL FUEL(LB) 
ALTITUDE(FT) NOX EMISS(LB) 
WEIGHT(LB) SEGMT TOTAL SEGMT 
START END SEGMT TOTAL 
422017. 
420897. 
1120. 
1866 . 
* H NUMBER 
SEGMENT 
+ T END 
TAXI OUT 
TAKE OFF 
t .300 
CLIMB 
+ 0 .750 
CRUISE 
* 0 .750 28000. 28000. 
RELEASE 275849. 0. 
.750 23000. 28000. 
225B49. 2OO0. 
+ 0 .750 28000. 28000. 
CRUISE 223849. 11860. 
28000. 28000, 
211989. 1537. 
28000. 0. 
MISSION SUMMARY *** 
TIME(MIN) DISTANCE(N MI) 
TOTAL SEGMT TOTAL 
419031. 6753. 
0. 28000. 
412278. 136429. 
+ 0 
REFUEL 
0 .750 
DESCENT 
0 .300 
RESERVES 
TAXI IN 
ZERO FUEL 
210453. 
193443. 
17010. 
149 . 
1120. 
2986 . 
9738 . 
.00 
146167. 
.00 
146167. 
,00 
148167. 
.00 
160027 . 
.00 
161564, 
. 00 
178573, 
, 00 
.00 
.00 
,00 
.00 
.00 
15 .0 
2.0 
11 .0 
541 .5 
,0 
105.C 
54 .4 
24 .1 
15.0 
17.0 
28 .0 
569 .5 
569. 5 
674.5 
728 . 9 
753 . 1 
755.1 
76 .3 
4023 .7 
.0 
.0 
404 . 6 
95 .4 
76.3 
4100,0 
4100.0 
4100.0 
4504.6 
4600.0 
DESIGN RANGE 
FLIGHT TIME 
4600.0 
736.1 
BLOCK TIME = 12.58 HOURS 
BLOCK FUEL = 161713.0 POUNDS 
TOTAL NITROGEN OXIDES EMISSIONS 
ATA TRAFFIC ALLOWANCE 
AIR MANEUVER = 44.6 
AIRPORT TRAFFIC ALLOWANCE =17.4 
AIRWAY DISTANCE FACTOR = 92.0 
0 . POUNDS 
154.0 NAUTICAL MILES 
MAC 
STAR 
.30 
.75 
.75 
,75 
.75 
.75 
C17-LONG-FLOPS-OUT 
ATA RANGE 4600.0 NAUTICAL MILES 
t DETAILED FLIGHT SEGMENT SUMMARY 
SEGMENT 1 CLIMB 
WEIGHT 
CLIFT 
419031. 
.82711 
.07425 
418702, 
.42319 
.02329 
418429. 
.28441 
418163. 
.27494 
.01690 
417897. 
.27909 
. 01709 
417631. 
.28232 
.01726 
417365. 
,26745 
.01685 
417098. 
.27513 
416826. 
.27285 
.01718 
416551. 
.27146 
.01724 
416272. 
.26448 
.01715 
415988. 
ALTITUDE 
LIFT 
ENERGY 
MACH NO. DELTA T 
L/D Q 
VELOCITY TIME 
DRAG SP RANGE 
0 . 
419031, 
1743 . 
37615. 
418702. 
3403 . 
23033. 
0. 
418429. 
5063 . 
25277. 
1287 . 
418163 . 
6722 . 
25705. 
2787 . 
417897. 
8382 . 
25591. 
4264 . 
417631. 
10042. 
25528. 
5394 . 
417365. 
11701. 
26289. 
6938 . 
417098. 
13361. 
26025. 
8276. 
416826. 
15020. 
26252, 
9616 . 
416551. 
16680. 
26455. 
10816. 
416272. 
18340. 
26986. 
12325, 
.3000 
11.140 
198.44 
.00350 
.4191 
18 . 178 
277.25 
.00483 
.5112 
16.554 
338.17 
.00583 
,5321 
16.268 
350.40 
.00620 
.5426 
16.330 
355.50 
.00649 
. 5543 
16.360 
361.25 
.00680 
.5815 
15.876 
377.44 
.00723 
.5901 
16 .027 
380.89 
,00770 
.6076 
15 .878 
390.33 
.00823 
. 6249 
15.746 
399.45 
.00876 
.6478 
15.425 
412.25 
.00928 
,6579 
NOX 
.00 
133 .3 
17.00 
.0 
. 35 
260. 2 
17 .35 
.0 
.28 
3 87 .2 
17 .63 
.28 
400.2 
17.91 
.0 
.29 
394 .0 
18.20 
.30 
389 .3 
18,43 
. 0 
,3C 
410 .7 
18.79 
.0 
.32 
399 .0 
19 .11 
,0 
.34 
402 ,C 
19.45 
.0 
.35 
403 .8 
19.80 
.0 
.37 
414 .2 
20.17 
.0 
.40 
DELTA D 
PCODE 
DIST 
ENG PAR 
. 0 
1 
,0 
,ooo 
1.4 
1 
1 . 4 
.ooo 
1.5 
1 
2.8 
.000 
1.6 
1 
4 . 4 
.000 
1.7 
1 
6.1 
.000 
1.7 
1 
7.8 
.000 
1.9 
1 
9.7 
.000 
2.0 
1 
11 .7 
.000 
2.1 
1 
13 .8 
.000 
2.3 
1 
16 .1 
.000 
2.5 
1 
18 . 6 
.000 
2 .7 
DELTA F THRUST FUEL PLOW EX POW 
FUEL T/TMAX SFC 
3315. 1.00000 .53438 
273. 
266. 
279 , 
DH/DT* 
0. 119703. 56725. 3936. 
2986. 1.00000 .47388 
329. 107400. 57392. 5657,4 
.0 
98916. 58017. 6026.9 
3588. 1.00000 .58653 .0 
266. 94961. 56515. 5877.0 
3854. 1.00000 .59513 4614.8 
91733. 54753. 5698.0 
4120. 1.00000 .59687 5232.2 
266. 88787. 53161. 5541.3 
4386. 1.00000 .59875 5001.C 
266. 85568. 52223. 5423.9 
4651. 1.00000 .61031 3735.5 
268. 80956. 49485. 5079.9 
4919. 1.00000 .61126 4887.6 
271. 76880. 47433. 4801.1 
5190. 1.00000 .61698 3981.5 
275. 73384. 45613. 4557.4 
5465. 1.00000 .62163 3779.8 
70506. 44417. 4364.7 
.01748 
415988. 
19999, 
26756. 
415696. 13817. 
.27889 415696, 
21659. 
26572. .01783 
415395. 
.29149 
415084 , 
.27877 
.01813 
414762. 
.28469 
.01350 
414425. 
,29379 
414070 
.32041 
.02001 
413694. 
.33431 
413288 
.35363 
.02169 
412843, 
.37458 
.02274 
412345. 
,39705 
412278. 
.39994 
.02407 
15420. 
415395, 
23319. 
26159, 
16444, 
415084. 
24978. 
27002, 
17881. 
414762. 
26638. 
26946. 
19497. 
414425. 
28298. 
26512. 
21253. 
414070. 
29957. 
25359. 
22820. 
413694. 
31617. 
25666. 
24475. 
413288. 
33277, 
25347 . 
26135. 
412843. 
34936. 
25064. 
27795. 
412345. 
36596. 
24839. 
2SO00. 
412278. 
36301. 
24815. 
15.548 
416.36 
.00990 
. 6688 
15.644 
420.38 
.01061 
. 6753 
15.880 
422.39 
,01141 
.7048 
15.373 
439.06 
, 01206 
. 7179 
15.392 
444.76 
.01285 
.7243 
15.632 
445.88 
,01384 
.7254 
16.013 
443.41 
.01490 
.7338 
16.119 
445.76 
.01596 
.7390 
16.305 
445.88 
.01726 
.7441 
16.471 
445.83 
.01857 
.7493 
16 . 601 
445. 88 
.02001 
.7500 
16.614 
445.88 
.02020 
SEGMENT 2 CRUISE 
402 .7 
20.57 
.0 
.43 
3 92 .3 
21.00 
.0 
,47 
375 .0 
21.47 
.0 
. 51 
391.8 
21 .97 
.0 
.55 
383 .4 
22 .52 
.0 
. 60 
365.0 
23 .12 
.0 
.69 
340.1 
23 . 81 
,0 
.78 
325.7 
24.59 
.0 
.91 
307.6 
25.50 
.0 
1 .07 
290.0 
26.57 
.0 
1 
273 
29 
3 
27.86 
.0 
.18 
271 .3 
28 .04 
.0 
1 
21.4 
.000 
3.0 
1 
24.3 
.000 
3.3 
1 
27 . 6 
.000 
3.6 
1 
31.3 
.000 
4.0 
1 
35.3 
,000 
4.5 
1 
39 . 8 
.000 
5.1 
1 
44.8 
.000 
5.8 
1 
50. 6 
. 000 
6.7 
1 
57.4 
. OOC 
3.0 
1 
65.3 
.000 
9.6 
1 
74 .9 
.000 
1.3 
1 
76 .3 
.000 
6029. 1.00000 .63120 3820.2 
292 . 
6321. 
301. 
6621 . 
311 , 
6932 . 
323 . 
7255. 
337. 
7592 . 
354. 
7946, 
376. 
8323 . 
406. 
8729 . 
445 . 
9174. 
498. 
9672. 
57 . 
9738. 
62731. 39663. 3707.5 
1.00000 .63227 3482.2 
58697. 37017. 3350.6 
1.00000 .63064 3409.3 
56680. 36405. 3179.1 
1. ooooo .64229 2013.8 
S3727. 34616. 2903.2 
5744. 1.00000 .62998 3224.7 
285. 66600. 42038. 4038.6 
WEIGHT 
CLIFT 
412278. 
ALTITUDE 
LIFT L/D 
ENERGY VELOCITY 
DRAG SP RANGE 
MACH NO. DELTA T 
0. 
TIME 
NOX 
28000. .7500 . 00 
DELTA D DELTA F 
PCODE 
DIST FUEL 
ENG PAR 
.0 0. 
1.00000 .64429 2634.8 
50191. 32224. 2580.0 
1.00000 .64203 2671,5 
46676. 29766. 2257.S 
1.OOOOO .63772 2560.0 
43833. 27928. 1982.4 
1.00000 .63715 2001.9 
40746. 25840, 1682.4 
1.00000 .63416 1827.4 
37996. 24006. 1414.3 
1.00000 .63180 1548.4 
35401. 22286. 1156.6 
1.00000 .62953 1285.5 
35080. 22073. 1124.2 
1.00000 .62921 1140.4 
THRUST FUEL FLOW EX POW 
T/TMAX SFC DH/DT* 
24815. 16566. 622 .2 
15:09:03 C17-LONG-FLOPS-OUT 
.39994 
. 02407 
396000. 
.38415 
.02337 
378000. 
.36668 
36O0O0. 
.34922 
.02191 
342000. 
.33176 
.02122 
324000. 
.31430 
.02057 
306000. 
.29684 
.01994 
288000. 
.27938 
.01934 
275849, 
.26759 
,01895 
WEIGHT 
CLIFT 
CDRAG 
225849. 
.21909 
,01747 
WEIGHT 
CLIFT 
223849 
.22715 
412278. 
36801. 
24815. 
28000. 
396000, 
36801. 
24096. 
2 8000. 
378000. 
36801. 
23328. 
2 8000. 
360000, 
36801, 
22590. 
28000, 
342000. 
36801. 
21879. 
28000, 
324000. 
36801. 
21200. 
28000. 
306000. 
3 6801. 
20553. 
28000. 
288000. 
36801. 
19938. 
28000. 
275849. 
36801. 
19540. 
16.614 
445.88 
.02691 
.750C 
16.434 
445.88 
.02753 
.7500 
16.204 
445.88 
.02821 
,7500 
15.936 
445.88 
.02890 
.7500 
15 . 631 
445 .88 
.02959 
. 7500 
IS.283 
445.88 
. 03026 
.7500 
14.888 
445.88 
.03093 
.7500 
14 . 445 
445.88 
.03160 
.7500 
14.117 
445.88 
,03204 
271 ,3 
28 .04 
.C 
59.59 
271.3 
87.63 
.0 
67 . 51 
271.3 
155.14 
.0 
69.16 
271.3 
224.31 
.0 
70.83 
271 ,3 
295.14 
. 0 
72 .48 
271.3 
367 . 61 
.0 
74.10 
271.3 
441.72 
. 0 
75 .72 
271 .3 
517.44 
.0 
52 . 06 
271 . 3 
569 . 50 
.0 
SEGMENT 3 RELEASE 
ALTITUDE MACH NO. DELTA T 
LIFT L/D Q 
ENERGY VELOCITY TIME 
DRAG SP RANGE NOX 
28000. 
225849. 
36801. 
18012. 
4 REFUEL 
.7500 
12.539 
445.88 
.03385 
.00 
271.3 
569.50 
. 0 
ALTITUDE MACH NO. DELTA T 
LIFT L/D Q 
ENERGY VELOCITY TIME 
DRAG SP RANGE NOX 
28000. .7500 105.00 
223849. 12.465 271.3 
36801. 445.88 674.50 
17959. .03391 .0 
2 
76.3 
,000 
442 .8 
2 
519 .1 
.000 
501.7 
2 
1020.8 
.000 
514 .0 
2 
153 4 .8 
.000 
52 6.3 
2 
2061 . 1 
, 000 
538. 6 
2 
2599 . 7 
.000 
550.7 
2 
3150.4 
.000 
562 .7 
2 
3713.1 
.000 
386.9 
2 
4100.c 
.000 
9738. .81372 .66758 .0 
16278. 24096. 16193. 729.8 
26017. .79013 .67204 .0 
18000. 23328. 15803. 856.2 
44017. .76495 .67743 .0 
18000. 22590. 15428. 991.6 
62017. .74074 ,68298 .0 
18000. 21879. 15070. 1137.6 
80017. .71745 .6B876 .0 
18000. 21200. 14734. 1295.5 
98017. .69518 .69501 .0 
18O0O. 20553. 14415. 1467.2 
116017. .67396 .70135 .0 
18000. 19938. 14111. 1655.3 
134017. .65379 .70776 ,0 
12151. 19540. 13917. 1793.4 
146167. .64073 .71224 .0 
DELTA D DELTA F THRUST FUEL FLOW EX POW 
FCODE 
DIST FUEL T/TMAX SFC DH/DT* 
ENG PAR 
4100.0 146167. 
.000 
18012. 
.59063 
13173. 
.73138 
2495.9 
.0 
DELTA D DELTA F THRUST FUEL FLOW EX POW 
PCODE 
DIST FUEL T/TMAX SFC DH/DT* 
ENG PAR 
, 0 
41OO.0 148167. 
.000 
17959. 
.58888 
13148. 
. 73211 
2529,0 
. 0 
SEGMENT 5 CRUISE 
WEIGHT 
CLIFT 
CDRAG 
223849. 
.22715 
.01742 
216000. 
.20953 
,01723 
211989 , 
.20564 
.01713 
SEGMENT 
WEIGHT 
CLIFT 
211989. 
.20564 
.01713 
211985. 
.21055 
211951 . 
.26089 
. 01811 
211912 
.34288 
211875. 
.50012 
.02975 
211848. 
.62413 
. 04150 
211823 
.57917 
211792. 
.55978 
ALTITUDE MACH NO. DELTA T 
LIFT L/D Q 
ENERGY VELOCITY TIME 
DRAG SP RANGE NOX 
28000. .7500 .00 
223849. 12.465 271.3 
36801. 445.88 674.50 
17959. .03391 .0 
28000. .7500 35.93 
216000, 12.164 271.3 
36801. 445,88 710.43 
17757. .03417 .0 
28000. .7500 18.51 
211989. 12.004 271.3 
36801. 445.88 728.95 
17659. ,03429 .0 
6 DESCENT 
ALTITUDE MACH NO. DELTA T 
LIFT L/D 5) 
ENERGY VELOCITY TIME 
DRAG SP RANGE NOX 
28000, 
211989. 
36801, 
17659, 
28000. 
212985. 
36596. 
17254. 
28000. 
211951. 
34936. 
14712, 
28000, 
211912 . 
33277. 
12869. 
28000. 
211875, 
31617, 
12602. 
2-7147 , 
211848. 
29957. 
14087, 
25447. 
211823. 
28298. 
13458. 
23850. 
211792, 
.7500 
12.004 
445.88 
.10258 
,7412 
12.286 
440.65 
. 10286 
.6658 
14.407 
395,83 
.10505 
.5807 
16.467 
345.24 
. 10978 
,4808 
16.813 
285.83 
. 14156 
.4223 
15.039 
251 .95 
. 19749 
.4223 
15.740 
253 ,74 
.15121 
.4148 
16.044 
. 00 
271.3 
728 . 95 
.0 
.06 
265.0 
729.00 
. 0 
. 52 
213 . a 
729.52 
.0 
. 68 
162.6 
730.20 
.0 
.86 
111.5 
731 .06 
.97 
89 .3 
732.03 
1 . 00 
96.2 
733.03 
.0 
1 .03 
99.6 
DELTA D DELTA F THRUST FUEL FLOW EX POW 
PCODE 
FUEL T/TMAX DIST 
ENG PAR 
4100.0 148167. 
. 000 
267,0 7849. 
2 
4367.0 156017. 
. 000 
137.6 4011. 
2 
4504.6 160027, 
.000 
17959. 
. 58888 
17757, 
.58228 
17659. 
,57907 
SFC 
13148. 
.73211 
13 050. 
.73489 
13002. 
.73626 
DH/DT* 
2529 . 0 
,0 
2662 .9 
. 0 
2734.2 
.0 
DELTA D 
PCODE 
DIST 
ENG PAR 
, 0 
0 
4504.6 
.000 
.4 
0 
4 505.0 
,000 
3 . 6 
0 
4508.6 
.000 
4 . 2 
0 
4512.8 
,000 
4 . 5 
0 
4517.3 
.000 
4.3 
a 
4521.7 
.000 
4 , 2 
0 
4525.8 
.000 
4.3 
DELTA F 
FUEL 
0 , 
160027, 
4. 
160031. 
35. 
160066. 
39 , 
160105. 
37. 
160142. 
27 , 
160169. 
25, 
160193. 
31. 
THRUST FUEL FLOW EX POW 
T/TMAX SFC DH/DT" 
0. 4346. -3761.4 
.00000 .00000 .0 
0, 
. ooooo 
0, 
.ooooo 
0 . 
.00000 
0. 
,00000 
4284 . 
.ooooo 
3768 . 
.00000 
3145 . 
.00000 
'3632 .1 
.0 
-2782,4 
.0 
-2123.2 
.0 
2019. -1721,7 
.00000 ,C 
0. 1276. -1696.6 
.00000 .00000 -878.5 
0. 1678. -1632.5 
.00000 .00000 -1704.6 
0. 1949. -1583.8 
Nov 18 96 
15t09:O3 C17-LONG-FLOPS-OUT 
26638, 
13200, 
22235. 
211755. 
24978. 
12932. 
20632 . 
211711. 
23319. 
12731. 
19003 . 
211660. 
21659. 
12521. 
17429. 
211602. 
19999, 
12433, 
15883, 
211537, 
18340. 
12397. 
14332. 
211464. 
16680. 
12364, 
12776. 
2113 84. 
15020. 
12332. 
11216. 
211296. 
13361. 
12303. 
9651. 
211201. 
11701. 
12274. 
8082 . 
211098. 
10042. 
12247. 
6508. 
210986. 
8332 . 
12220. 
4930. 
.46894 210866. 
6722 . 
.02712 12193. 
.03489 
211755. 
.53774 
.03284 
211711. 
.51956 
.03124 
211660. 
.49743 
.02943 
211602. 
.48755 
.02865 
211537, 
,48452 
.02840 
211464. 
.48176 
,02817 
211334. 
.47922 
.02796 
211296. 
.47688 
.02777 
211201. 
.47470 
. 02759 
211098. 
.47257 
.02742 
210986. 
.47081 
210866. 
210738. 3336 . 
.46370 210738. 
5063 . 
.02673 12148. 
250.93 
.12873 
.4088 
16.374 
248.93 
.11044 
. 4020 
16.629 
246.36 
.09649 
,3971 
16.904 
244.92 
.08434 
.3382 
17.019 
240.94 
.07496 
.3773 
17.063 
235.57 
.06747 
.3667 
17.104 
230.30 
.06120 
.3564 
17.141 
225.IS 
. 05588 
.3464 
17.175 
220.12 
.05131 
.3367 
17.207 
215.21 
. 04733 
.3273 
17,237 
210.41 
.04385 
.3182 
17.266 
205.73 
,04077 
.3094 
17.294 
201.19 
.03803 
.3020 
17.348 
197.46 
.03560 
734.06 
.0 
1.06 
103 .6 
735.12 
.0 
1.09 
107 .2 
736.21 
.0 
1.12 
112.0 
737.33 
.0 
1.14 
114.2 
738.48 
.0 
1 .17 
114 .9 
739.65 
.0 
1 .20 
115 .5 
740.85 
.0 
1.23 
116 .1 
742.08 
.0 
1.26 
116 . 6 
743.35 
.0 
1 .29 
117.1 
744.64 
. 0 
1 . 
117 , 
745.97 
. 0 
.33 
.5 
.36 
.9 
1. 
117. 
747.33 
.0 
1.39 
118.3 
748.72 
1 . 
119 . 
750.14 
. 0 
.42 
. 6 
4530.2 
.000 
4.4 0 
4534 . 6 
.000 
4.5 
0 
4539 . 1 
.000 
4,6 
0 
4543 .7 
.000 
4 . 6 
0 
4548.3 
.000 
4 . 6 
0 
4552.9 
,000 
4.7 
0 
4557.6 
.000 
4.7 
0 
4562.3 
.000 
4.7 
0 
4567.0 
.000 
4 .7 
0 
4571.6 
.000 
4 .7 
0 
4576.3 
.000 
4 .7 
0 
4581.0 
.000 
4.7 
0 
4585.8 
.000 
4 .1 
0 
4590.5 
.000 
160224 . 
37 , 
160262. 
44 . 
160305 . 
51 . 
160356 . 
58 . 
160415. 
66 . 
160480. 
73 . 
160553. 
80 . 
160633. 
38. 
160720, 
95 . 
160816. 
103 , 
160919. 
Ill , 
161030. 
120. 
161150. 
129 . 
161279. 
. OOOOO 
o. 
.ooooo 
o. 
.ooooo 
o. 
,00000 
o. 
.ooooo 
O, 
.00000 
0 , 
.ooooo 
0 . 
.00000 
0, 
.ooooo 
0 . 
. ooooo 
0 . 
, ooooo 
0. 
. ooooo 
0. 
. ooooo 
0 . 
.ooooo 
.00000 -1547.5 
2254. -1539.5 
.OOOOO -1520.C 
2553. -1500.3 
.00000 -1468.4 
2904. -1467.2 
.00000 -1455.7 
3214. -1433.7 
.00000 -1375.6 
3492. -1398.1 
.00000 -1319.2 
3763. -1363.6 
. OOOOO -1290.5 
210600. 1718. 
.45252 210600. 
3403 . 
12076. .02595 
4029. -1330.2 
.00000 -1262.7 
4290. -1297.9 
.00000 -1235.5 
4547, -1266.6 
,00000 -1209.1 
4799. -1236.2 
.00000 -1183.2 
5046. -1206.7 
.00000 -1157,9 
5290. -1178.1 
.00000 -1133.6 
5547. -1152.7 
,00000 -1119.3 
210453. 0. 
,41540 210453. 
1743 . 
.02359 11950, 
, 2967 
17 . 439 
195.07 
.03341 
.300C 
17.611 
198.44 
.03177 
1.45 
122.5 
751.59 
.0 
1.46 
133 .3 
753 .05 
.0 
138. 
4595.2 161417, 
.000 
147. 
4600.0 161564. 
.000 
0. 
.00000 
0. 
.ooooo 
5839. 
.OOOOO 
6246 . 
.00000 
-1132.8 
-1114.1 
-1141.1 
-1177.2 
« DH/DT IS THE AVERAGE OVER THE STEP. 
+• ND OF THE STEP. 
SOBJ/VAR/CONSTR SUMMARY 
FUEL RANGE VAPP FAROFF FARLDG 
* SW TR SWEEP TCA VCMN CH 
178573.4 4600.0 110.0 4290. 5046. 69501 
+ 800.0 .000 25.00 .1210 .750 45000. 111.1 
DESIGN - TIT OPR FPR BPR TTR 
+• ALT THRUST SFC OVEFF CDT ' CDP 
2800.0 30.800 1.5000 5.9000 1.0000 
+ 45000. 3832. .6129 .2963 1259.6 85.47 
VAPP= 110.0 
FAROFF- 4290. 
FARLDG = 5046. 
THE OTHER DATA ARE INSTANTANEOUS AT THE E 
AMFOR SSFOR 
W/S T/W 
35764. 
.386 
(SLS) 
THRUST 
422016.6 7.200 40700.0 3 
VJET (CRUISE) MACH 
30.8 1673.8 
Appendix F Page 59 
Appendix F. F16C ACSYNT Input & Output File 
5 DATA BLOCK A 
***** GENERAL DYNAMICS F-16C FIGHTER -
S DATA BLOCK B 
1,0,0,0,0,0,0 
$ DATA BLOCK V 
END 
FIGHTER 
COMBAT AIR PATROL 
5 5 5 570 570 1 0 1 2 0 
0 0001 0 . 80 36000.00 0 00 0.00 
1 2 3 4 6 
1 2 3 4 6 
1 2 3 4 6 
GENERAL DYNAMICS F-16C BLOCK 30 GEOMETRY ***** 
0. 
2.114, 
1.570, 
0.035, 
1, 
1.294, 
1.067, 
0.030, 
0.000, 
. FALSE., 
799, 
001, 
900, 
I, 
AREA 
SWEEP 
TCROOT 
XWING 
AREA 
TAPER 
XHTAIL 
SIZIT 
AREA 
TAPER 
VTNO 
ZROOT 
BODL 
FRATIO 
SFPACT 
300.000, 
32.183, 
0.040, 
0.468, 
63.700, 
0 .390, 
0.974, 
. FALSE. , 
54 . 
0. 
1 
1 
47 
12 
1 
750, 
437, 
000, 
000, 
580, 
524, 
466, 
DIHED 
SWFACT 
TCTIP 
ZROOT 
SWEEP 
TCROOT 
ZROOT 
SWEEP 
TCROOT 
XVTAIL 
KSWEEP 
DRADAR 
FRN 
WFUEL 
0.000, 
0.690, 
0.040, 
0.000, 
32.271, 
0.060, 
0.000, 
43.225, 
0.O53, 
0.950, 
1. 
2.600, 
4.801, 
32.000, 
49.000, FRAC 
1, 
1.000, WFUEL 13732.000, 
F16-ACSYNT-IN 
SWING 
AR = 3.OOO, 
FDENWG = 49.000, 
TAPER = 0.228, 
WFFRAC = 0.326, 
KSWEEP = 1, 
SEND 
$HTAIL 
AR 
SWFACT 
TCTIP 
KSWEEP 
5 END 
SVTAIL 
AR 
SWFACT 
TCTIP 
YROOT 
SIZIT 
SEND 
$FUS 
BDMAX 
FRAB 
LRADAR = 5.900, SFPACT = 1.466, WFUEL = 137 
SEND 
SCREW 
MCREW 
SEND 
SFUEL 
DEN 
SEND 
SENGINE 
N 
SEND 
SS$$SS$S$SSSSS$SS$S$S$SSSSSSS$S$$$SSS$SS$$$$$S$$$SS$S$S$SSS$S$SS$SS$SSSS$S$5S$?S 
STRDATA 
0.000, 
= 1.000, 
= 74.000, 
0.000, 
= 1900.000. 
= 1.000, 
2, 
= 1, 
0. 
2, 
CRMACH 0 850, DESLF 9 000, FRFURE 
RANGE 644 000, TIKTOl 6 OOO, TIMT02 
ULTLF 13 500, WFEXT = 6760 000, WFTRAP 
WFUEL 6972 000, HMAXP = 50000 000, HMINP 
SMMAXP = 2 000, SMMINP 0 300, OMAX 
THRSET = 0 285, WKLAND 0 574, WCOMBP 
IBREG 1, IENDUR = 1, I PLOT 
IPSTOl 6, IPST02 2, MMPROP 
MILCOM = 0, LEGRES = 0, KERROR 
MODLND 1, NCODE 2, NCRUSE 
IPSIZE = -2, LENVEL .FALSE., 
SEND 
10 0 0E+03 
PHASE 
MACH NO, 
START END 
ALTITUDE 
START END 
HORIZONTAL 
DIST TIME 
NO. 
TURN 
VIND 
'G'S WKFUEL M IP IX W B A P 
CLIME 0 87 0 00 -1 32500 -1 0 0 0 0 0 0 0 1 oooo 1 3 -1 0 0 0 0 
CRUISE 0 87 0 87 -1 33750 -1 0 0 0 0 0 0 0 1 oooo 1 6 0 0 0 0 0 
LOITER 0 80 0 80 28500 2850C 0 0 120 0 0 0 0 0 1 oooo 1 -3 0 0 0 0 0 
COMBAT 0 90 D 90 10000 10000 0 0 1 0 0 0 5 0 1 oooo 1 1 0 1 0 1 0 
COMBAT 0 90 0 90 10000 10000 0 0 1 0 0 0 5 c 1 oooo 1 1 0 0 0 0 0 
CLIMB 0 00 0 00 10000 44500 -1 0 0 0 0 0 0 0 1 oooo 1 3 0 0 0 0 3 
CRUISE 0 87 0 87 -1 0 -1 0 0 0 0 0 0 0 1 oooo 1 4 0 0 0 0 0 
LOITER 0 40 0 40 1 0 0 0 20 0 0 0 0 0 1 oooo 1 4 0 0 0 0 0 
CLIMB 0.50 0.00 
CLIMB 0.60 0.00 
0 10000 
-1 20000 
-1.0 
-1 .0 
0.0 
0.0 
0.0 
0.0 
1.0000 
1.0000 
oooo 
oooo 
Unmatched 
SACHAR 
ABOSB 
BDNOSE 
RALOIT 
ROCAN 
SPANAC 
XCDC 
ALELJ 
ISUPCR 
ELLIPC 
SMNSWPI 
SMNSWPI 
SMNSWPI 
CLO(2) 
CLO(5) 
CLO(8l 
CLOC(1) 
CLOC(4) 
CLOC (7) 
CLOC(10 
CLOW (3 ) 
CLOW(6] 
CLOW(9) 
CMO(2) 
CMO(5) 
CM0I8) 
YSWP(l) 
YSWP(4) 
YSWP(7} 
YSWP(1C 
SEND 
SAJMULT 
CSF 
FCDF 
FCDWB 
FLBCOR 
FCDO 
FCDRA (2 
FCDRA {5 
FCDRA(8 
SEND 
SATRIH 
FLDM(1) 
FLDM(4] 
FLDM(7) 
FLDM(10 
FVCAM (3 
FVCAM(6 
FVCAM (9 
ITRIM(2 
ITRIMI5 
ITRIM{8 
CAND 
IT 
SPANF 
SEND 
SADET 
Aerodynamics Cor F16-C 
3) = 
6) = 
9) = 
150, 
000, 
000, 
020, 
,000, 
0,600, 
3, 
0, 
FALSE . , 
0.400, 
1.O00, 
1 . 600, 
0 .000, 
0.000, 
0.000, 
o.ooo, 
o.ooo, 
0.000, 
0.000, 
o.ooo, 
0.000, 
.000, 
.000, 
.000, 
.000, 
.000, 
.000, 
.000, 
.000, 
1 .000, 
1.000, 
ooo, 
DOO, 
ooo, 
ooo, 
1.000, 
ALMAX = 
BTEF 
RCLMAX 
SFWF 
SWPMAX 
XCDW 
1NORM 
ITRAP 
SMNSWP (1) •• 
SMNSWP(4) = 
SMNSWP(7J : 
SMNSWP(IO)= 
CLO(3) 
CLO(6) 
CLO(91 
CLOC(2) 
CLOC(5) 
CLOC(8) 
CLOW(1) 
CLOW(4) 
CLOW(7) 
CLOWUO) = 
CMO(3) 
CMO(6) 
CMO(9) 
YSWP(2) 
YSWP (5) 
YSWP(8} 
ESSF 
FCDL 
FENG 
FLECOR 
PLD 
FCDRA(3) 
FCDRA(6) 
FCDRA(9) 
10.000 
1 . 000 
1 .000 
1.000 
60.000 
0.600 
1 
0 
o.ooo 
0 . 600 
1 .200 
1.800 
0 .000 
o.ooo 
0.000 
0.000 
0. 000 
0.000 
o .ooo 
o.ooo 
0 .000 
o.ooo 
0.000 
o .ooo 
o.ooo 
o.ooo 
0.000 
0.000 
720, 
ooo, 
000, 
000, 
ooo, 
000, 
000, 
000, 
AMC 
MACHN 
ROC 
SMNDR 
SWPMIN 
AJCAN 
ISMNDR 
IXCD 
SMNSWP(2) 
SMNSWP(51 
SMNSWP (8) 
CLO(1) 
CLO(4) 
CLO(7! 
CLO(10) 
CLOC(3) 
CLOC(6) 
CLOC(9) 
CLOW(2i 
CLOW(5) 
CLOW(8) 
CMO (1) 
CMO(4) 
CMO(7) 
CMO(10) 
YSWP(3) 
YSWP(6) 
YSW(9) 
FCD 
FCDW 
FINTF 
FMDR 
FCDRA(1) 
FCDRA(4) 
FCDRA(7) 
FCDRA(IO) 
40.000, 
0.750, 
0.015, 
0.900, 
0.000, 
0, 
0, 
1, 
0.200, 
0 .800, 
1.400, 
o.ooo, 
0.000, 
0 .000, 
0.000, 
o.ooo, 
0.000, 
0, 000, 
o.ooo, 
o.ooo, 
0 .000, 
0.000, 
0.000, 
0.000, 
0.000, 
0.000, 
0.000, 
0.000, 
1.000, 
1.000, 
1.000, 
1 .ooo, 
1.000, 
1.000, 
1.000, 
1.000, 
0 000, FLDM(2) 0 000, FLDM(3) 0 ooo. 
0 000, FLDM(5) = 0 ooo. FLDM(6) = 0 ooo, 
0 000, FLDM[8) 0 000, FLDM(9) 0 000, 
0 ooo, FVCAM(1) = 0 000, FVCAM{2) = 0 ooo, 
0 000, FVCAM ( 4) = 0 000, FVCAM(5) = 0 ooo. 
0 000, FVCAM(7) = 0 ooo, FVCAM(8) = 0 ooo, 
0 ooo, FVCAM!10) = 0 ooo, ITRIM(l) = 0, 
0, ITRIM(3) = 0, ITRIM(4) = o, 
0, ITRIMI6) = 0, ITRIM{7) = 0, 
0, ITRIMI9) = 0, ITRIM(IO) = 0, 
0 000, CFLAP 7 ooo, CGM 0 360, 
0 ooo, SFLAP 70 000, SM = 0 000, 
10 ooo, ZCG 0 000, IVCAM - 0, 
Nov IS 96 j 
15:07:51 ! 
I PLOT i. NALF - 10, NMDTL - 10, 
ICOD I . IALF - 0, IALP - 2, 
SMN(l) = 0 400, SMN(2) - 0 600, SMN(3) = 0 800, 
SMN(4) 0 850, SMN[5) = 0 900, SMNI6) 0 950, 
SMN(7) 1 050, SMN(81 1 200, SMN{9) = I 400, 
SMN(IO) 1 600, ALIN(l) = c 000, ALIN(2) l 000, 
ALIW[3) 2 ooo, ALIN 14) = 3 000, ALIN (51 = 4 000, 
ALIN(6) 5 000, ALIN(7) 10 ooo, ALIN(8) = 20 000, 
ALIN{9) = 30 000, ALIN(IO) = 40 000, ALTV(l) 30000 000, 
ALTV(2) 30000 000, ALTV(3) 30000 000, ALTV(4) 3000C 000, 
ALTV(5) 3OO00 000, ALTV(6) 30000 ooo, ALTV(7) 30000 000, 
ALTV(8) 30000 ooo, ALTV(9) = 30000 000, ALTV(IO) 30000 000, 
CLINPT(l) 0 000, CLINPT(2) = 0 000, CLINPT(3) 0 000, 
CLINPT(4) 0 000, CLINPT(5) 0 000, CLINPT16) = 0 000, 
CLINPT17) 0 ooo, CLINPT(8) 0 000, CLINPT{9) = 0 000, 
CLINPT(10) = 0 ooo, ITB(1) 0, ITB(2) 0, 
ITB(3) = 0, ITB(4) 0, ITB(5) 0, 
ITB(6) 0, ITB(7) 0, ITB(8) 0, 
TTB(9; 0, ITBI10) = 0, ITS(l) 0, 
ITS(2] 0, ITS (3) = 0, ITS(4) = 0, 
ITS(5) 0, ITS(6) = 0, ITS(7) 0, 
ITS(8) = 0, ITS(9) 0, ITS(IO) 0, 
ISTRS(l) 0, ISTRS(2) 0, ISTRS(31 = 0, 
ISTRS(4) = 0, ISTRS(5) = 0, ISTRS(6) = 0, 
ISTRSI7) 0, ISTRS(8) = 0, ISTRS(9) 0, 
ISTRS(IO) 0, 
SEND 
LDRAG 
ICDO = 0, SMNCDO(1) 0 000, SMNCDO(2) = 0 000, 
SMNCDO(3) = 0 ooo, SMNCDO(4) 0 ooo, SMNCDO(5) 0 000, 
SMNCDO(6) 0 ooo, SMNCDO(7) = 0 000, SMNCDO(8) = 0 ooo, 
SMNCDO(9 ) 0 ooo, SMNCDO(10) 0 000, CDONPT(1) 0 ooo, 
CDONPT(2 ] 0 ooo, CDONPT(3) 0 ooo. CDONPT(4) 0 000, 
CDONPT(5) = 0 000, CDONPT(6) 0 000, CDONPT(7) 0 000, 
CDONPT(8) = 0 ooo, CDONPT(9) = 0 000, CDONPT(10) 0 000, 
SMNBMB(l) 0 ooo, SMNBMB(2) = 0 200, SMNBMB(3) = 0 400, 
SMNBMB(4) 0 600, SMNBMB(5) 0 800, SMNBMB(6) = I 000, 
SMNBMB(7) I 200, SMNBMB(8) i 400, SMNBMB(9) = I 600, 
SMNBMB(10) - i 800, CDBMB (1) 0 ooo, CDBMB(2) = 0 000, 
CDBMB{3) 0 000, CDBMB(4) 0 000, CDBMB(5) = 0 000, 
CDBMB(6) 0 ooo, CDBMB(7) = 0 000, CDBMB(8) 0 000, 
CDBMB(9) 0 000, CDBMB110) = 0 000, SMSTRS(1) 0 000, 
SMSTRS<2) 0 200, SMSTRS(3) = 0 400, SMSTRS(4) 0 600, 
SMSTRS(5) 0 800, SMSTRS(6) 1 000, SMSTRS(7) i 200, 
SMSTRS(8) = l 400, SMSTRS(9) 1 600, SMSTRS(10) = I 800, 
CDSTR(1) 0 390, CDSTR(2) = 0 000, CDSTR(3) 0 000, 
CDSTR(4) 0 000, CDSTR(5) 0 000, CDSTR(6) = 0 000, 
CDSTR(7) 0 000, CDSTR(8) = 0 000, CDSTR{9) = 0 000, 
CDSTR(10) 0 000, SMTANK(11 = 0 000, SMTANK(2) 0 200, 
SMTANK (3) 0 400, SMTANK(4) 0 600, SMTANK(5] = 0 800, 
SMTANK(6) = 1 ooo, SMTANK17) 1 200, SMTANK{81 1 400, 
SMTANK ( 9) 1 600, SMTANK(10) 1 800, CDTNK (1) 1 800, 
CDTNKI2) 0 000, CDTNK(3) 0 000, CDTNK(4) = 0 ooo, 
CDTNK(5) 0 000, CDTNK(61 = 0 000, CDTNK (7) = 0 ooo. 
CDTNK(8) 0 000, CDTNK(9) = 0 000, CDTNK(IO) 0 000, 
SMEXTR(1) = 0 000, SMEXTR(2) 0 200, SMEXTR(3 1 = 0 400, 
SMEXTR(4) 0 600, SMEXTR[5) 0 800, SMEXTR(6) 1 000, 
SMEXTR(7) = 1 200, SMEXTR(8) = 1 400, SMEXTR(9) 1 600, 
SMEXTR(10) = 1 80O, CDEXTR(1) 0 000, CDEXTR(2) = 0 ooo, 
CDEXTR(3) 0 000, CDEXTR(4) = 0 000, CDEXTR(5) = 0 000, 
CDEXTR(6) 0 000, CDEXTR(7) = 0 000, CDEXTR(8) 0 000, 
CDEXTR(9) 0 000, CDEXTR(10] 0 ooo, 
SEND 
TAKE 
CLLANE = -l 000, CLTO -1 000, DELFLD = 45 000, 
DELFTO 45 000, DELLED = 30 000, DELLTO = 30 000, 
LDLAND -l ooo, LDTO = -1 000, 
F16-ACSYNT-IN 
SEND 
SAPRINT 
ECHOIN 
IPBLNT 
IPEXT 
IPINTF 
IPWAVE 
SEND 
»»***« F100 
1, 
= 0, 
0, 
0, 
0, 
CYCLE ANALYSIS 
ECHOUT 
IPCAN 
IPFLAP 
IPLIFT 
KERROR 
0, INTM 
0, IPENG 
0, IPFRIC 
0, IPMIN 
SLEWIS 
YREN 80. 000, TWAB = 24850 000, TWOAB = 14880 000, 
TWTO = 1 . ooo, PRFD 1 000, P12P1 = 3 120, 
P2P1 25 000, SCPR = 1 280, T3 = 2743 ooo. 
RI OA -1 ooo, SFINSP 1 ooo, ALT I 0 000, 
AM 0. 000, AUAENG 0 005, AWAENG = 0 260, 
KMT 1. 000, SFADP 1 ooo, SFADSP 1 000, 
ALTD (1) 0. ooo. ALTD(2) = IOOOO 000, ALTD(3) = 20000 000, 
ALTD(4) = 30000. 000, ALTD(5) = 40000 000, ALTD(6) = 50000 000, 
XMACH (1) 0 000, XMACH(2) = 0 450, XMACH(3) 0 750, 
XMACH(4) 0 900, XMACH (5) 1 200, XMACH(6) 1 500, 
DEPWCC 2 .00, XMDES 2 200, EN = 1, 
I PR = -3, KT5 = 2, KT7 2, 
IPRINT 0, NAB 5, NEWINL 0, 
MODPRT 1, 
SEND 
= 35388.OOO, IDELT 
SAFTBD 
SEND 
FIGHTER 
GENERAL DYNAMICS F-16C BLOCK 30 WEIGHTS, CAP MISSION 
SOFTS 
WGTO 
SEND 
SFIXW 
WBODY 
HNA 
WCA 
WGEAR 
WSC 
WCREW 
WBB1 
WETANK 
SEND 
3624.000, 
688.900, 
312.000, 
172.000, 
730.000, 
215.000, 
0.000, 
1529.000, 
WHT 
WVT 
WELT 
WHDP 
WE 
WAMMUN 
WBOMB 
WWING 
498.000, 
376,100, 
2413.500, 
311.000, 
3911.100, 
103.000, 
172.000, 
2096.000, 
WLG 
WAIRC 
WEP 
WINST 
WFS 
WARM 
WMISS 
992.000, 
267.000, 
686.000, 
107.000, 
578.000, 
808.500, 
1066.OO, 
Nov 18 H 
15:07:52 : 
CCCCCCC OOOOOOO PPPPPPP EEEEEEE SSSSSSS 
C 0 OP P E S 
C 0 0 P P E
C O O PPPPPPP EEEE SSSSSSS 
C OOP E S 
C P
CCCCCCC OOOOOOO P EEEEEEE SSSSSSS 
CONTROL PROGRAM 
FOR 
ENGINEERING SYNTHESIS 
TITLE 
***** GENERAL DYNAMICS F-I6C FIGHTER - COMBAT AIR PATROL ***** 
CARD IMAGES OF CONTROL DATA 
CARD IMAGE 
1| $ DATA BLOCK A 
2) «*«** GENERAL DYNAMICS F-16C FIGHTER - COMBAT AIR PATROL 
3) S DATA BLOCK B 
4) 1,0.0,0,0,0,0 
4) 1 0 0 0 0 
5) $ DATA BLOCK V 
6 I END 
TITLE: 
>**** GENERAL DYNAMICS F-16C FIGHTER - COMBAT AIR PATROL ***** 
CONTROL PARAMETERS, 
CALCULATION CONTROL, NCALC = 1 
NUMBER OF GLOBAL DESIGN VARIABLES, NOV = 0 
NUMBER OF SENSITIVITY VARIABLES, NSV = 0 
NUMBER OF FUNCTIONS IN TWO-SPACE, N2VAR = 0 
NUMBER OF APPROXIMATING VAR. NXAPRX = 0 
INPUT INFORMATION PRINT CODE, IPNPUT = 0 
DEBUG PRINT CODE, IPDBG = 0 
F16-ACS YNT-OUT 
ESTIMATED DATA STORAGE REQUIREMENTS 
INPUT 
9 
REAL 
EXECUTION 
9 
AVAILABLE 
5000 
INPUT 
1 
INTEGER 
EXECUTION 
1 
AVAILABLE 
1000 
AAAAAAA CCCCCCC SSSSSSS Y Y N N 
A A C S Y Y NN N 
A A C S Y Y N N N 
AAAAAAA c SSSSSSS Y N N N 
A A c s Y N N N 
A A c s Y N N 
A A ccccccc SSSSSSS Y N N 
T 
T 
T 
T 
T 
T 
NASA-AMES PROGRAM 
FOR 
AIRCRAFT SYNTHESIS 
TITLE 
***** GENERAL DYNAMICS F-16C FIGHTER - COMBAT AIR PATROL **** 
AIRCRAFT TYPE - FIGHTER 
1 TITLE: 
***** GENERAL DYNAMICS F-16C FIGHTER - COMBAT AIR PATROL *«** 
AIRCRAFT TYPE - FIGHTER 
CONTROL PARAMETERS: 
READ CONTROL, MREAD = 5 
EXECUTION CONTROL, MEXEC = 5 
WRITE CONTROL, MWRITE = 5 
NUMBER IDENTIFYING CONVERGENCE 
VARIABLE FOR CONVERGED VEHICLE, IOBJ = 570 
CALCULATION CONTROL, NCALC 
VALUE MEANING 
1 SINGLE ANALYSIS 
2 OPTIMIZATION 
3 SENSITIVITY 
4 TWO-VARIABLE FUNCTION SPACE 
5 OPTIMUM SENSITIVITY 
6 APPROXIMATE OPTIMIZATION 
i 
15:07,52 F J 6-ACS YNT-OUT 
NUMBER IDENTIFYING COMPARISON 
VARIABLE FOR CQHVEMJEP VEHICLE, JQBJ = 
SUMMARY OUTWIT PRINT COPE, XFSUM = 
:: • h/.L ERROR PRINT CODE, KGLOBP = 
GLOBAL COMMON INITIALIZATION CODE, 1NTT . 
DEBUG PRINT CODE, IPDBQ = 
GLOBAL PLOT CONTROL, IOPLT -
DATA TRANSFER INFORMATION FILE, 1RDDTR 
•ATA TRANSFER INFORMATION PRINT, IPDTR 
VEH [CLE rONVERGENCE INFORMATION: 
CONVERGENCE TOLERANCE, "."OL .1O000E-03 
ESTlH WCALC VS MEET SLOPE - 800QOE+O0 
BOUNDING WEIGH'!1, W3MAX - .360OOE*05 
570 
1 
2 
0 
MODULE IJBNTIFXCATIOH NUMBERS : 
NUMBER MODULE 
1 GEOMETRY 
2 TRAJECTORY 
3 AERODYNAMICS 
4 PROPULSION 
5 STABILITY AND CONTROL 
0 WEIGHTS 
H StiKJC MOM 
9 EIONOMICS 
:I SUMHAKY OUTPUT 
: 0 TAKEOFF AND 1.AHV1NG 
KWJLES ARE CALLED FOR INPUT IN THE FOLLOWING ORDER: 
I 2 3 4 G 
MODULES ARE CAI.LEP FOR EXEC'J'i 1ON IN I'HE FOLLOWING ORDER: 
1 2 3 4 6 
MODULES ARE CJM-LE!J FOR OUTPUT IN THE FOLLOWING OfiPtlR: 
1 2 3 4 6 
TNI,j! FOR '• . .. 
GEOMETRY LANPI^T DALD 
;••»«* GtUh>.-.-: LYNAMICS F-16C BLOCK 30 GEOMETRY 
2 $W • 3 
3 AK 
4 RIJ-.M-JG 
5 TAi'ER 
6 WFFRAC 
7 KSWEEP 
8 SEND 
3.000. ASF.A 
49.000, SWEEP 
0-328, TCHOOT 
0.326, XWING 
1, 
300 000, Blh'KlJ 
32.1 83 , SWFACT 
0.040, TCilP 
0.468, ZROOT 
0.000, 
0.690, 
0.O4O, 
0. 000, 
9 SHTJIIL 
10 AT: 
11 SVIFACT 
12 TCTIP 
13 KSWEEP 
14 SEND 
15 SVTAIL 
16 AR 
17 SWFACT 
18 TCTIP 
19 YROOT 
20 KIZIT 
21 SEND 
22 SFUS 
2.3 I! DMAX 
24 E . 
25 LRADAR 
2 6 ?END 
27 &CREH 
28 NCREW 
29 SEND 
30 SFUEL 
31 DEN 
32 SEND 
33 $ENGINE 
34 N 
35 SEND 
END OF GEOMETRY DATA CARDS 
3 5 LINES READ 
NOTE; FRATIO = BODL'BEWAX 
GSSO-.KTRY FNITLSL OUTPUT 
Fuselage Defiriltion 
2.114, hl'.l-.k 
1.570, TAPER 
0.035, XHTAIL 
1, SIZIT 
1.294. AREA 
1.067, TAPJ0R 
0.03 0, VTNO 
0.000, ZROOT 
FALSE. , 
3.799, BODL 
3.001, FRATIO 
5.900, SFFACT 
1, 
49.000, FRAC 
63.700, SWEEP 
0.39O, TCROOT 
0.974, ZROOT 
. FALSE., 
54.750, SWEEP 
0.437, TCROOT 
1.000, XVTAll, 
1.000, KSWEEP 
47.5BO, DRAPAR 
12.524, FRN 
1.466. WFUEL 
1.000, 
32.271, 
0.060, 
0,000, 
43,225, 
0,051, 
0.950, 
1, 
2 
4,801, 
13730.600, 
12 .000. 
X 
.00 . u 
Area 
,00 
F16-ACS YNT-OUT 
91 33 .35 
1 82 55 .94 
2 74 73 1. 66 
3 65 88 2.45 
i 56 1 02 3.28 
5 47 1 15 4 .13 
6 38 1 26 4 .97 
1 30 1 36 5.80 C
O 21 1 45 6 . 60 
9 12 1 53 7.36 
10 03 1 60 8
 .07 10 94 1 
67 8.73 
11 86 1 72 9 .32 
12 77 1 77 9 . 84 
13 68 1 81 10.29 
14 59 1 84 10.66 
15 50 I 87 10.95 
16 42 1 89 11.17 
17 33 1 90 11 .29 
18 24 1 90 11.34 
20 03 1 9C 11.34 
21 83 1 90 11 .34 
23 62 1 90 11.34 
25 42 1 90 11.34 
27 21 1 90 11 .34 
29 00 1 90 11.34 
30 80 1 90 11 .34 
32 59 1 90 11.34 
34 39 1 90 11.34 
36 18 1 90 11 .34 
36 75 1 91 11 .47 
37 32 1 92 11.52 
37 89 1 91 11 .49 
38 46 1 90 11 .37 
39 03 1 ST 11 . 16 
39 60 1 86 10.87 
40 17 1 83 10 .49 
40 74 1 79 10. 03 
41 31 1 74 9 . 49 
41 88 1 68 8
 . 88 42 45 1 61 8.19 43 02 1 54 7 .44 
43 59 1 45 6 .64 
44 16 1 36 5.78 44 73 1 25 
4 . 88 45 30 1 12 3 .96 45 87 98 3 .02 
16 44 82 2 ,1C 
47 01 62 
1.19 47 58 30 .28 Fuselage 
Max. Diameter.. 
Fineness Ratio. 
Surface Area.., 
Volume 
3 . 799 
12.524 
704.477 
413.928 
Geometry Initial Output 
Dimensions of Planar Surfaces (each) 
Wing H.Tail V.Tail Canard Uni ts 
NUMBER OF SURFACES. 1. 0 1.0 1 .C 1,0 
PLAN AREA 30O.O 63.7 54 . a .0 
I SQ.FT. SURFACE AREA 333 .1 115 .3 
116 . 9 .0 (SQ.FT. 
VOLUME 79 .6 13 .3 11.6 .0 (CU.FT. 
SPAN 30.000 11.604 8 .417 .000 (FT. ) 
L.E. SWEEP 39.992 39.999 
C/4 SWEEP 32 . 183 32.271 
T.E. SWEEP .038 .498 
ASPECT RATIO 3.000 2.114 
ROOT CHORD 16.2 87 7.898 
ROOT THICKNESS 7.818 5.687 
ROOT T/C .040 .060 
TIP CHORD 3 .713 3 .080 
TIP THICKNESS 1.782 1.294 
TIP T/C . 040 , 035 
TAPER RATIO .228 .390 
MEAN AERO CHORD.... 11.317 5.842 
LE ROOT AT 18.196 38.445 
C/4 ROOT AT 22.267 40.419 
TE ROOT AT 34.482 46.343 
LE M.A.C. AT 23.169 40.523 
C/4 M.A.C. AT 25.998 41.983 
TE M.A.C. AT 34.486 46.364 
Y M.A.C. AT 5.928 2.477 
LE TIP AT 30.779 43 .313 
C/4 TIP AT 31.707 44,083 
TE TIP AT 34.492 46.393 
ELEVATION .000 .000 
GEOMETRIC TOTAL VOLUME COEFF .300 
EFFECTIVE TOTAL VOLUME COEFF .300 
47.499 
43.225 
25.907 
1 . 294 
053 
758 
053 
956 
424 
030 
437 
837 
36.148 
38.411 
45.201 
40.141 
41.850 
46.978 
3.659 
45.333 
46.322 
49.289 
1.900 
, 096 
.096 
.000 (DEG.) 
.000 (DEG.) 
.000 (DEG.) 
,000 
.000 (FT,: 
. 000 (IN. ) 
,000 
.000 (FT.) 
.000 (IN.) 
,000 
. 000 
.000 (FT.I 
.000 (FT.) 
.000 (FT.) 
,000 (FT.) 
.000 (FT.) 
.000 (FT.) 
.000 (FT.) 
.000 
.000 (FT.) 
.000 (FT.) 
.000 (FT.) 
,000 (FT.) 
. 000 
. 000 
EXTENSIONS 
Strake 
Centroid location at ,00 
Area .0
Sweep Angle .0
Wetted Area 0 
Volume .0
Total Wing Araa 300.00 
Total Wetted Area 1269.81 
FUEL TANKS 
Tank Volume Weight Density 
Wing 24. 1153. 49.00 
Fus#l 257. 12579. 49.00 
Fus#2 0. 0. 50.00 
Total 13732, 
Rear Extension 
.00 
.00 
.00 
.00 
Mission Fuel Recnjired = 
Available Fuel Volume in Wing = 
13732. 
72 . 
Aircraft Weight = 
Aircraft Volume = 
Aircraft Density = 
.000 lbs. 
518.418 cu.ft. 
.000 lbs./cu. ft. 
ICASE = 8 (Fineness Ratio Method) 
Input for Module ft 2 
TRAJECTORY INPUT 
TIMTOl =6.0 
TIMT02 =1.0 
FRFURE = .00 
DESLF =9.00 
MENDUR = 0 . 
QMAX = 1900. 
XDESC - 80.0 
WKFUEL = 1.000 
NCRUSE = 2 
IPSI2E =-2 
IPSTOl - 6 
IPST02 = 2 
IPLOT = 2 
HMINP = 0. 
HMAXP - 50000. 
DELHP = 4000. 
15:07:52 F16-ACSYNT-OUT 
ULTLF =13.50 CRMACH .850 IBREG = 1 SMMINP = .300 FLECOR 1 .000 ISMNDR 0 LDTO = -1.000 
RANGE 644 . WKLAND = .574 IENDUR - 1 SMMAXP - 2.000 FLNOSE i.ooc ISUPCR = 0 MACHN .750 
WFUEL 6972. FLFAC = .600 IPRINT = 0 DELMP = . 100 
1 
FLSCOR = 1.000 ITRAP * 0 QHOQ1 .000 
WFEXT 6760. DEC EL = .250 KERROR = 0 WCOMBP 1 00 FMDR 1.000 IVCAM 0 RCLMAX 1.000 
WFTRAP = 74 . NLEGCL = 0 NLEGCR = 0 NLEGLO = 0 FSEP = 1.000 IXCD = 1 ROC .015 
FWGMAX = 1.200 TOL = .001 MILCOM = 0 NMISS = i FTRIM = 1.000 KERROR 0 SFWF 1.000 
NCODE = 2 
MMPROP = 1 
ARRAYS 
ALIN - .000 1.000 2 .000 3 .000 4 . 000 5.000 10.000 20.000 30.ooc 
MISSION 1 + 40.000 
ALTV = 30000. 30OO0. 30000. 3 0000. 30000. 30O0O. 30000. 30000. 30000, 
MACH NO. ALTITUDE HORIZONTAL NO. VINE 4 30000. 
PHASE START END START END DIST TIME TURN "G"S WKFUEL M IE IX 1} 6 A P CDBMB .oooo .0000 .0000 .0000 .oooo .0000 .0000 .0000 . oooo 
+ . 0000 
CLIME ,50 .00 0 100OO -1.0 .0 .0 .0 1.0000 1 3 -1 0 0 0 0 CDEXTR .0000 .0000 . oooo .0000 .0000 .0000 .0000 . oooo .0000 
CLIMB .60 .00 -1 20000 -1.0 .0 .0 .0 1.0000 1 3 -1 0 ooo 4 .0000 
CLIMB .87 .00 -1 32500 -1.0 .0 .0 ,0 1.0000 1 3 -1 0 ooc CDONPT . oooo .0000 .0000 .oooo .oooo ,0000 .oooo .oooo . oooo 
CRUISE . 87 .87 -1 33750 -1.0 . C .0 . 0 1.0000 1 4 0 0 0 0 0 4 ,0000 
LOITER . 80 ,80 28500 2 8500 .0 120.0 .0 .0 1.0000 1 --3 0 C 0 0 0 CDSTR = .3900 . oooo .oooo . oooo .oooo .0000 .0000 .oooo . oooo 
COMBAT . 90 . 90 IOOOO IOOOO .o i.o .0 5.C 1.0000 1 1 0 1 0 10 4 .0000 
COMBAT .90 , 90 10000 10000 .0 1.0 .0 5.0 1.oooo 1 1 o o 0 0 0 CDTNK = 1.8000 .0000 ,0000 .oooo . oooo .0000 .0000 . oooo .0000 
CLIMB .00 .00 10000 44500 -1.0 .0 .0 . 0 1.0000 1 3 0 0 0 0 0 4 .0000 
CRUISE . 87 .87 -1 0 -1.0 .0 .0 . 0 l.oooo 1 4 0 0 ooo CLINPT .000 .000 .ooo .000 .000 .000 .000 .000 .ooo 
LOITER .40 .40 1 0 ,0 20.C . 0 .0 1.0000 1 4 0 0 0 0 0 4 , 000 
CLO = .000 .ooo .000 .000 .000 . ooo .000 .ooo .000 
4 .000 
CLMIN .000 .ooo .000 .ooo .000 . 000 .ooo .ooo .ooc 
4 .000 
CMO = .000 . 000 .000 .000 .000 .000 .000 .ooo .000 
4 .000 
FCDRA = 1.000 1 .000 1 .000 1.000 1 .000 1 .000 1.000 1 .ooo 1.000 
4 1 .000 
Input for Module » 3 FCLRA 1 .000 1.000 1.000 1.000 1.000 1.000 1.000 1.000 i .ooo 
*********** ****** **************************** * * * * ******* ************* * * * * ** * * * + 1. 000 
AERODYNAMIC INPUT DATA FLDM = .000 .000 .000 . ooo .000 .ooc .OOC .ooc .ooo 
4 .000 
FVCAM = .000 .000 .000 .000 , 000 . 000 .000 .000 .000 
4 .000 
ISTRS 0 0 0 0 0 0 0 0 0 
FACTORS INTEGERS AND LOGICALS REALS 4 0 
ITB = 0 0 0 0 0 0 0 0 0 
FALEL 1 OOO ALELJ = 3 NALF = 10 ABOSB = .150 SHK 4 0 
= 25 000 ITS = 0 0 0 0 0 0 0 0 0 
FBLNT = 010 IALF = 0 NMDTL = 10 ALMAX 10 .000 SM + 0 
= ooo ITRIM 0 0 0 0 0 0 0 0 0 
FCD 1 000 IALP 2 ECHOIN = I AMC 40 .ooo SMNDR 4 0 
= 900 SMEXTR = .ooo .200 , 400 . 600 . 800 i .ooo 1.200 1 .400 1.600 
FCDF 1 000 I AXE = O ECHOUT - 0 BTEF 1 ooo SWPMA + 1.800 
= 60 ooo SMN = .400 . 600 .800 . 850 .900 .950 1.O50 1.20C 1.400 
FCDL l ooc ICDO = 0 ELLIPC = F CGM = 3 60 SWPMI 4 1.600 
= ooo SMNBMB .000 .200 .400 . 600 . 80C 1.000 1.200 1 . 400 1. 600 
FCOLH I ooo ICOE 1 ELLIPH = F CLLAND -1 .000 YO 4 1 . 800 
= ooo SMNCDO .ooo .000 . ooc .000 .000 .000 ,000 .000 .000 
FCDO i ooo INORM = 1 ELLIPW = F CLTO -1 000 ZCG 4 .000 
= ooo SMNSWP .000 . 200 .400 . 600 .800 1.000 1 .200 1 .400 1.600 
FCDW 1 000 INTM 0 CSF 1 ooc 4 1 . 800 
FCDWB 1 000 IPBLNT 0 DELFLD 45 ooo SMSTRS = , ooo .200 , 400 .600 . 800 1 . 000 1 .200 1.400 1 .600 
FCL 1 000 I PENG 0 DELFTO 45 000 4 1.800 
FCLH 1 ooo IPFRIC = 0 CELLED = 30 000 SMTANK = .ooo .200 .400 .600 .800 l.OOC 1.200 1.400 1. 600 
PDNOSE 1 ooc IPTEXT 0 DELLTO = 30 ooo + 1 . 800 
FENG 1 000 IPINTF 0 ESSE = 720 YSWP = .000 .ooo .000 .000 . 000 .000 .000 .ooo .000 
FEXP 780 IPLIFT 0 EXA 667 4 .000 
FINTF 1 000 I PLOT 1 EXC = 2 000 
FLBCOR 1 ooo IPMIN 0 IT = ooo 
FLD 1 000 IPWAVE 0 LDLAND -1 000 
Nov IK 
15:07:52 
Input for Module # 4 
F16-ACSYNT-OUT 
******** 
PROPULSION INPUT 
VERSION 04-76 
•**•** F100 CYCLE ANALYSIS ************ 
AENDIA 000 AENLE = 000 AENWT 000 
ALT I 000 AM = 000 ATURB 328 
AENTW = 000 
AUAENG = 005 AWAENG = 260 BA = 730 
DELPR 000 DELT57 = 100 000 DEPWCC = 2 000 
DIA1 = 3 800 EAB1 750 EB1 = 940 
EDI 750 ETAC1 = 800 ETAF1 = 820 
ETAT1 = 900 HTR 600 HVF 18600 000 
MACH1 = 1 000 
MACH 2 
= 1 100 PCDFAC = 1 ooc 
POSA = 8 903 PRFD 1 000 PWCC 100 OOO 
P11P1 3 120 F2P1 = 25 ooc R10A -1 000 
R32 = 940 R54 = 920 R54N = 880 
R7U - 930 R711N 980 SCPR 1 280 
SFADP 1 000 SFAJDSP 1 000 SFAUXP 1 ooo 
SFBEP = 1 000 SFBPP 1 000 SFBTP 1 000 
SFDIVP 1 000 SFINSP = 1 000 SPIP - 1 000 
SFSFC1 = 1 000 SFSFC2 = 1 ooo SFSFC3 - 1 000 
SMI = 500 SODG = 1 000 TOSA - 412 000 
Til 520 000 TWAB = 24! 150 . TWOAB 14880. 
TWTO = 1 000 T3 = 2743 . T5M - 3400. 
TS1 = 0. T7M = 3' 00. T71 0 . 
VC1 980 WCWA1 = 018 XMDES - 2 200 
XMT = 1 000 YREN 80 . FRBT - 000 
FRPN - 000 RDIAM - 1 150 RLENG = to 000 
I PR _ -3 IPRINT _ c I PLOT _ 0 
KERROR 0 KODE = 2 KT5 2 
KT7 2 MINPR 0 NAB 5 
NOZZ 1 NPROP 6 NSUMM 15 
I ENG 2 
THESE VARIABLES ARE USED BY TABLE LOOK UP 
ESF = 1.000 NDTAIL = 0 IPDBUG = 0 
ALTD = 
XMACH = 
XMPRI = 
XPRI = 
XMPRI1 = 
,000 
XPRI1 = 
.000 
XMPRI2 = 
.000 
XPRI2 = 
.000 
0 . 
. 000 
.000 
I.OOO 
. 000 
.000 
.000 
.ooo 
.000 
.ooc 
.000 
,000 
10000. 
.450 
.300 
1.000 
.000 
. 000 
.ooc 
.000 
, 000 
. 000 
.ooo 
.000 
20000. 
.750 
.600 
1.000 
.000 
.000 
. 000 
.000 
30000, 
.900 
.900 
i .ooo 
.ooc 
.000 
.000 
.000 
40000. 
1.200 
1 .200 
1.000 
.ooo 
.ooo 
.000 
.000 
(TF30) 
50000. 
Input for Module it 6 
************************* 
AIRCRAFT TYPE: FIGHTER 
TITLE: 
.500 
.000 
.000 
.000 
.000 
.ooo 
.000 
.ooo 
.000 
.000 
INITIAL WEIGHTS INPUT DATA 
ACSYNT MODULE NUMBER 6 
********** 
OCONTROL OPTIONS 
I PRINT = 
IDELT = 
Kl 
K5 
KB = 
FR 
STRESS = 
•PCABIN : 
IMNTEN = 
TECHI = 
SLOPE 11) = 
SLOPE 19) = 
SLOPE(18) 
1 I GRAPH 
1 IOBLIQ 
1.00 K2 
1.00 K6 
.00 KP1 
1.50 TECHG 
30000. 
5.00 IGEAR 
0 IMTGR 
1 .00 
1.00 
1 .00 
I.00 
= 1 
1. 00 
1 .00 
1.00 
1 .00 
1 ITAIL = 
0 KWING = 
1.00 K3 
1.00 AFMACH -
.00 KP2 
00 WGTO 
DENS 
1 JFLTYF 
1 
1 .00 1 
1,00 1 
1. 00 1 
i. oo 
0 KERROR 
0 KBODY 
1.0 K' 
.00 MAXIT 
.00 
35388, 
,100 
1 
= C 
= 1 
= 1.0 
= 1 
FLIFTF = .000 
. 00 
.00 
.00 
.00 
,00 
00 
00 
00 
00 
.00 
. 00 
,00 
l. oo 
1.00 
0INITIAL ESTIMATES 
IF CODE = 1, WEIGHT IS FIXED 
QUANTITY VALUE CODE QUANTITY VALUE CO 
WAF 10616 0 WAIRC 267. 1 
WAPU 0 0 WAMMUN = 103 . 1 
WARM 808 1 WBAG - 0 . 0 
WBB1 0 0 WBODY 3624 , 1 
WCAND = 0 0 WCARGO = 0. 0 
WCREW = 215 1 WE 3911. 1 
WELT = 2414 1 WEP = 686. 1 
WETANK = 1529 1 WFEQ - 4884 . 0 
WFS 573 1 WCA 312 . I 
WGEAR - 172 1 WHDP 311, l 
WHT 498 1 WINST = 107. i 
WLG = 992 1 WMISS = 1066, l 
WNA 689 1 WPA = 0. 0 
WPASS 0 0 WPL = 4211 . 0 
WPS — 4884 0 WSC = 730. 1 
WTSUM 35388 0 WVT 376. 1 
WWING = 2096 1 WBOMB - 172 . 1 
WENVP 0 0 WPIV 0. 0 
WLIFTF 0 0 WBB2 = 0. 0 
WTHRV - 0 0 
******** ***************** ************** * * ********** ********* 
** Begin Vehicle Convergence ** 
Estimated Gross Weight = .35388E+05 
Calling Module * 1 
Calling Module # 2 
Calling Module # 3 
Calling Module t 4 
Calling Module # 6 
Calculated Gross Weight = .35388E+05 
** End Vehicle Convergence ** 
1 Convergence Iterations Required 
************************************************************** 
Calling Module # 1 
Calling Module 8 2 
Summary of Non Fatal Errors encountered in cycle analysis 
P5 < P6S 3 times 
0 RANGE CALC RESULTS : 1 .644O00OE+03 -.8438086E+03 
Summary of Non Fatal Errors encountered in cycle analysis 
P5 < P6S 3 times 
0 RANGE CALC RESULTS : 2 .5940000E+03 -.5330762E+02 
Summary of Non Fatal Errors encountered in cycle analysis 
.6940000E+03 
.5906282E+03 
Nov 18 96 
15:07:52 F16-ACS YNT-OUT 
P5 < P6£ 3 times 
0 RANGE CALC RESULTS : 3 .5906282E+03 -.4029688E+02 .5B01852E+03 
Summary of Non Fatal Errors encountered in cycle analysis 
P5 < P6S 3 times 
0 RANGE CALC RESULTS : 4 .58O1852E+03 .3466797E+01 .5810125E+03 
Summary of Non Fatal Errors encountered in cycle analysis 
P5 < P6S 3 times 
Calling Module # 3 
Calling Module ft 4 
Calling Module # 6 
Output for Module # 1 
Fuselage Definition 
X R Area 
3 65 88 2 45 
4 56 1 02 3 28 
5 47 1 15 4 13 
6 38 1 26 4 97 
7 30 1 36 5 80 
21 1 45 6 60 
9 12 1 53 7 36 
10 03 1 60 8 07 
10 94 1 67 8 73 
11 86 1 72 9 32 
12 77 1 77 9 84 
13 68 1 81 10 29 
14 5S 1 B4 10 66 
15 50 1 87 10 95 
16 42 1 89 11 17 
17 33 1 90 11 29 
18 24 1 90 11 34 
20 03 1 90 11 34 
21 83 1 90 11 34 
23 62 1 9C 11 34 
25 42 1 90 11 34 
27 21 1 90 11 34 
29 00 1 90 11 34 
30 80 1 90 11 34 
32 59 1 90 11 34 
34 39 1 90 11 34 
36 18 1 90 11 34 
36 75 1 96 12 09 
37 32 2 02 12 78 
37 89 2 07 13 40 
38 46 2 11 13 94 
39 03 2 14 14 39 
39 60 2 17 14 74 
40 17 2 18 14 99 
40 74 2 19 15 14 
41 31 2 20 15 17 
41 88 2 19 15 08 
42 45 2 18 14 88 
43 02 2 15 14 54 
43 59 2 12 14 08 
44 16 2 07 13 47 
44 73 2 01 12 72 
45 30 1 94 11 82 
15 87 1 85 10 74 
16 44 1 74 9 46 
17 01 1 59 7 90 
47 S8 1 32 5 48 
Fuselage 
Max. Diameter 3.799 
Fineness Ratio 12.524 
Surface Area 758.223 
Volume 473.188 
F16-ACS YNT-OUT 
DiBsnsiana at Planar Surfaces leach] 
Wing H.T-ail V.Tail C*nnrd Units 
NUMBER OF SURFACES. 3.0 1 .0 1.0 1 .0 PEAK AREA IOC .0 .7 5/ . 0 (vO.FT SURFACE AREA... 311.1 1 L5 . 3 
116 . 9 .0 (SQ.FT VOLUME H ' 3.3 11.6 .0 (CU.FT SEAN 3 0.000 11 . 604 8 .417 . ooo jFT. ) 
L.E, SfcEEP 
39.992 3 9 . 999 47 .499 . ooo (11KG. ) 
a'•! iv.'!;E? 
... 32.183 32 .271 " .22b .ooo (DEG.1 
T . E . S'viEEP . .... .03:1 .4*8 25 . 907 .000 (DEC. i 
ASPECT HATIO . . 3,000 2 11 1 1 . 2 : ,0D0 
ROOT CHORD ... 16.287 7 . 898 9 .053 . 000 (PT. ) 
ROOT THICKNESS. 7 . 818 5 ,637 5 .758 .000 1 IN . ) 
ROOT T/C -040 .060 . 053 .000 
•. IP CHORD. .... 3.713 3 .080 i . 956 .ooo 1 FT. | 
TIP THICKNESS.. 1.782 .294 I .424 .000 UN. ) 
TIP T/C .040 .035 .030 .000 
TAPER FLATtQ , , . .228 .390 . 437 .ooo 
HEAN AERO CHORD . . . 11.317 LB42 6 .837 .ooo (FT, 1 
LE ROOT AT 18.190 445 76 . 148 .000 (PT. ) 
C •' i ROOT AT .... 22.267 40 .419 3P 411 .000 (FT. ) TE r::-:it AT 
... 34.4Ri 4i. .343 65 .201 .000 (PT. ) 
LE M.A.C. A'-' . . . ... 23.1B9 4" .522 40.141 .ooo (FT . ) 
C/4 M.A.C. AT.. ... 25.99E 41 .983 41 .850 .ooo (FT. ) 
TP M.A.C. AT.,. J4.4m; 46 364 ii .976 .ooo (FT. ) 
V M.A.C. AT.... 
S.93S 7 .477 :• •yr .ooo 
LE TIP AT ... 30.779 '3 313 45 .333 .000 (FT. ) 
C/4 TIP AT 3 L 707 ii 
0*3 
46 .122 .•oo (FT . ) 
TE TIP AT ... 34,492 14 393 .219 • 00 (FT, ) 
LLEVAT; :-N .D0Q 000 1 .9130 . ooo (FT. ) 
.0: ::,::iRlc itai VOLUKE COEPF 
300 
0»6 
.000 
EFFECTIVE TOTAL VOLUME
 COj..! •-, 300 .096 .000 
EXTENSIONS 
Cuntroid location at 
Ares ' .. .) igl j 
Vie L ted Area Volu."'^ 
Total wing Area 
T-jtal Watted Area 
Wing 
Fus»I Total 
FUEL 
VrJui 
TANKS 
Wei ght 
24. 1151. 
19. SB19. 
o. o. 
6972 . 
Scrake 
.00 
, 00 
.00 
, 00 .00 
300.00 
1323.55 
49 00 
49 . 00 
50.00 
Rear Extension . 00 .00 
.00 , 00 
Mission Fuel Required = 
AVSi lab] i? Fuel VoJUil\£ in Wing 
697 2 . 
72 . 
Aircvatt neiyht 
Alzcraft Volume -
Aircra.lt Dftrtnity = 
35386.0UU lbs. 
577 . 6" 8 a. ft.. 
61.259 lbs./Cl 
Output for Module # 2 
ICAS (Fineness Ratio Moirhcdl 
* * * . 4 + * 
'* * v J * * * 1 4 * « 1 *******T TRAJECTORY OUTPUT 
MISSION 
1 (PAYLOAD = 
3678. LB) 
PHASE K H CL ALPHA WFUEL TIME VEI. 
SFC 11 
THRUST (11 CP W Q 
SFC [Vr TFiRUSTlUl CDINJI L/l: 
T.. I'HA PR X WARM-UP 0. 
405 . 9 6 .00 
2 .51 1611 . TAKEOFF .27 0 . 1 .5541 
12 ,00 247 .3 1 00 301 . .92 16433. . 68B1 9 -56 405 2
 L-109 . .92 16438. .OOUO 2 . 26 1 .00 1 .00 4707 . 
2ND SEG .27 400 . ' . 5541 12 .00 301. .92 
0. 6881 39 .85 34734.8 405 29 IDS. . 32 1S41R. 
.001 > 2 .26 L.0B 00 
CLIMB .91 10001). . 1340 1 .:, 
164 . 6 . 60 977 . 1.07 3 491 1 , . 02: •; . 34570.2 4 04 S38 . Cycle 
. 01 0 . .oooo 
.95 1.00 1 .00 6 . 
CLIMB .91 20000. ,1987 3 ;•>:: ? . 78 S39. 1 .01 
11431. 0251 . 12 
3)407 . 4 
280 .63 558. 
Cycl e . 00 ' . . uooo 7 .98 1 .00 / . 
CLIMB 
l. to 32500. .2343 2 . 0 8 299.2 2 .00 1086 . 1
 01 8842 . • 0S07 2 . 62 3410:-. 7 207 . 93 479 . Cyc li> ,0o 0 . . oooo • -64 .97 1 .00 19 . 
CRUISE . 87 33528. .3822 4 . 57 1329..-: 3" . I 852 . .90 
40Bli . .0476 .00 33179.1 143 .77 38H>. 
Cycle .00 0 . .0.01 n 8 .02 .53 1 .00 359. 
LOITER . SO 28500. .3554 ' u 
7156.6 120 -0D soi. .93 3915 . . 0432 25022.4 169 . 93 302. Cycl e .00 
(• . uooo 8 .23 .45 1 .Ii
 1 
949 . 
COMBAT . 90 10000. .4975 6 . .; •; 411.5 I .017 97D. 
1 . 3"-? 17717. . 0 711 4 . 90 22912.9 401 .31 K2 5 Cycle .00 0 . .0000 6 . 99 1.19 1 . oo 10. 
COMBAT .90 ii'ooo. .4379 5 . )3 21.1 .2 1 970 . 
1.02 
12407, .0499 8 . 1$ 21701.7 : 83 . :.j P2 5 , 
Cycle .00 0 . .0000 R 77 83 1 .Cl 10. 
CLIMB 
1 . j0 44500. . 1941 1 . 62 319, i 2 .64 1 255. :...)- JJLl . 0142 5 .59 2 13(32 . J 145 - 9 3
 7 i . 
Cycle . 00 0. . OOOO 5 , 68 .97 . . ' 24 , 
CRUISE .a- 45J15. 
. 42 4 3 5 . . i 3214.9 
•'• • .93 342 . 
. 59 2293 . .0475 . 0 
201&7,4 
'dv. . 2 ii 162 . 
Cycle .00 0. . 0000 8 .84 .51 1  0L 291 . 
GOITER . it 1 • .2836 3 . lb 1350.4 20 . 00 447 . 
2 . 32 1611. . 0226 .00 18017.1 34J .-- 237 . Cycle .00 0. .0000 12 . 52 . 10 1 oo 86 . 
LANDING .26 0 . 1 .5557 12 .00 290 . . 92 164 
. 6B07 .22 2754B.3 403 100. 
92 0. . oooo 2 9 I. DO : . ,30 JC7D . 
F16-ACSYNT-0UT 
Pue1 Summary Total Fuel Mission Fuel 
Reserve Fuel Trapped Fuel 
13112. 
13873 
• . 7* . TaReott Fuel: Waihiup = Takeoff = Fuel L''.TLI : External Internal S760. 5972 . SMNSWP set lnrcrr*ctly in AerodynamicE facetting to bound the Mach numj»r. 
ADDITIONAL COMBAT PARAMETERS CONDITIONS PS Nl ttttT RADIUS ALPHA • eo 
3 G FLIGHT 1013.9 1,00 .00 0. 1.02 . 101 .0216 
H- 1UU0D. SUSTAINED .0 * . 92 13 , 02 42&S 5.24 . 498 0711 MAX. INST. 
-190.9 7.IS It.at 3957. 10.00 .731 .1451 COMBAT ENERGY = .SP8J38EtOS K> .913 1 G FLIGHT 
125. 1 1.D0 .DO 0 . . 90 ,069 .0131 H-iooao. SUSTAINED .0 8.17 15.41 3605. 5.33 .438 .0439 MAX. INST, 
-12T.7 8.SI 16.07 
345R. 10.00 .731 .1370 COMBAT ENERGY •750699E-05 
Output lor Madula * , 
BI cj-Lk Tima - 3 .677 hrs Block Range ii 1661.7 Block FU»1 - U372.y lb. 
TakeoEE Field Length (total runl r 4707. ft Landing Field Length (total r-jril - 8070. li Landing Field Length (ground runl = 40B0, Ft 
Weight tor Landing calculation = 27545. lbs Landing Thrust to Weight ratio 11 .537 Takeoff Weight 35338. lbs Landing Weight 
iaai7. lbs 
15:07:52 
Mach 
Altitude 
1 .40 
30000. 
Parasite Drag 
Takeoff 
Induced 
Configuration: 
Drag 
Flaps and Slats 
F16-ACSYNT-OUT 
Friction .0095 Alpha Cl Cd L/D Cm e Cdtrim Deltrim 
Zone 
Body .0051 0 251 1449 1 7 -.110 .06 .0000 . 0 
6 
Wing . 0022 1 0 337 1607 2 1 -.121 . 10 .0000 .0 
Strakes .0000 2 0 423 1768 2 4 -.131 . 14 . 0000 .0 
6 
H. Tail .0011 3 0 SOS 1943 to 6 -.142 . IB .0000 .0 
V. Tail .0011 4 0 595 2136 2 8 - . 152 .22 . oooo .0 
6 
Canard 
c 
,0000 5 0 681 2351 2 9 -.163 .25 .0000 . 0 
0 
Interference . 0004 10 0 1 099 3779 2 9 - .212 .38 ,0000 .0 
6 
Wave ,0182 20 0 1 851 8472 2 2 -.280 .45 .0000 .0 
External .0000 30 0 2 325 1 4732 1 6 - .281 .40 .oooc ,0 
Tanks .0000 40 0 2 62 5 2 3248 1 1 - .253 .32 .0000 .c 
6 
Bombs 
Stores 
Extra 
Camber 
.0000 
.0000 
.0000 
.0000 
Cdmin 
Et 
Mach 
Altitude 
1 . 60 
30000. 
Parasite Drag 
Slope Factors 
Cl/Alpha (per radian) 
Cdl/Cl"2 
Alpha Transition 2one 2-3 
Flap Setting 
Slat Setting 
Flap Type Single 
Landing Configuration: Flaps and Slats 
Induced Drag 
3 .4016 
.3313 
1. 064 
45 . 
30 . 
42. sq. 
Friction 
Zone 
Body 
. 0090 
.0048 
Alpha 
.0 
Cl 
167 
Cd 
. 1090 
L/D 
1.5 
Cm 
-.073 
e 
.04 
Cdtrim 
, oooo 
Deltrim 
.0 
6 
Wing .0021 1 0 246 . 1224 2 0 - . 083 ,08 .OOOC .0 
6 
Strakes . 0000 2 0 326 . 1358 2 4 -.093 . 12 .0000 .0 
H. Tail 
£ 
.0011 3 c 406 . 1503 to 7 - .102 .16 . 0000 .0 
0 
v. Tail .0010 4 0 487 .1666 2 9 -.111 .20 .OOOC .0 
6 
Canard . 0000 5 0 567 .1851 3 1 - .121 ,23 .0000 .0 
6 
Interference .0004 10 0 964 .3134 3 1 - .166 .36 .0000 .0 
• 
Wave .0176 20 0 I 699 .7604 2 2 -.226 .42 .oooo .0 
6 
External .oooo 30 0 2 199 1 .3948 1 6 -.225 ,38 .oooo .0 
6 
Tanks . oooo 40 0 2 527 2.2604 1 1 - .198 .31 .0000 .c 
6 
Bombs 
Stores 
Extra 
. 0000 
. 0000 
. 0000 
Slope Factors 
Cl/Alpha (per radian) 3.3805 
Cdl/Cl"2 .3476 
Alpha Transition Zone 2-3 .500 
Camber .0000 
Cdmin 
ft 
. 0399 
Flap Setting 
Slat Setting 
Flap Type Single 
45. 
30. 
42 . 
Detailed Aerodynamics Output 
Nov 18 96 
15:07:52 F16-ACSYNT-OUT 
Mach 
Alti tude 
. 4C 
30000. 
Parasite Drag Induced Drag 
Friction .0114 Alpha Cl Cd L/D Cm e Cdtrim Deltrim 
Zone 
Body 
2 
. 00S1 .0 .000 . 0128 0 .000 ,00 . oooo . 0 
Wing 
2 
.0026 1 0 .077 .0136 5 7 .004 , 87 .0000 .0 
Strakes .oooc 2 0 . 153 . 0157 9 a .008 . 87 .0000 .0 
2 
H. Tail ,0013 3 .0 .228 .0192 11 9 .011 .87 .0000 .0 
V. Tail .0013 4 0 301 .0239 12 5 .014 .87 . oooo .0 
2 
Canard .0000 5 0 374 0298 12 5 . 016 .87 .oooo . 0 
Interference . 0014 IC 0 675 .1149 5 9 ,019 . 47 .0000 .0 
3 
Wave ,000C 20 0 1 133 .4018 2 a -.013 .35 .0000 .0 
3 
External . oooo 30 0 1 364 7966 1 7 -.071 .25 .0000 ,0 
J 
Tanks 
. oooo 40 0 1 299 1 1445 1 l -.115 .16 .0000 .0 
3 
Bombs ,0000 Slope Factors 
Stores .0000 Cl/Alpha (per radian) 1.8610 
Extra . oooo Cdl/Cl "2 .6704 
Alpha Transition Zone 2- 3 6.267 
Camber . oooo Programmed Flap Setting 0. 
Cdmin .0128 Flap Type Single 42 . sq 
Et 
Mach = . 60 
Altitude = 30000. 
Parasite Drag Induced Drag 
Friction .0112 Alpha Cl Cd L/D Cm e Cdtrim Deltrim 
Zone 
Body . 0060 0 000 0199 0 .000 .00 .0000 .0 
2 
Wing .0026 1 0 082 0207 4 . 0 .003 .88 .0000 .0 
C 
Strakes .0000 2 0 163 0231 7 . 0 .005 .38 ,0000 .0 
H, Tail 
2 
.0013 3 0 242 0270 9. 0 .007 , 88 . oooo .0 
\!. Tail .0013 4 0 321 0344 9 . 3 .003 .75 .0000 .0 
£ 
Canard .0000 S c 3 84 0479 8 . 0 ,010 .56 .0000 . 0 
Interference . 0014 10 0 685 1279 5. 4 . 0O6 .46 . oooo .0 
3 
Wave .0000 20 0 1 162 4315 2 . 7 - .033 .35 .oooc . 0 
3 
External . oooo 30 0 1 405 8445 1, 7 -.096 .25 . oooo ,0 
j 
Tanks .0000 40 0 1 350 1 2042 1. 1 -.119 .16 .0000 .0 
3 
Bombs 
Stores Extra 
.0000 
.0000 
. oooo 
Slope Factors 
Cl/Alpha (per radian) 1.9343 
Cdl/Cl~2 .6495 
Alpha Transition Zone 2-3 4,151 
Camber 
Cdmin 
* ft 
.0000 Programmed Flap Setting 
Flap Type Single 
Detailed Aezodynamics output 
15:07:52 F16-ACS YNT- OUT 
Detailed Aerodynamics Output 
Mach 
Altitude 
.80 
30000. 
parasite Drag Induced Drag 
Friction .0108 Alpha Cl Cd L/D Cm e Cdtrim Deltrim 
Zone 
Body 
2 
.0058 0 000 .0196 0 .000 ,00 , oooo .0 
Wing 
2 
. 0025 1 0 091 . 0206 1. 4 .001 . 88 .0000 .0 
Strakes . oooc 2 0 180 .0235 7. 1 .003 .88 .0000 . 0 
2 
H. Tail 
2 
. 0013 3 0 26a .0300 8. 3 .003 .73 ,0000 .0 
V. Tail .0012 4 0 335 .0401 8 . 3 .003 . 58 .0000 . 0 
3 
Canard .0000 5 0 401 .0507 7 . 9 .002 .55 .oooo .0 
3 
Interference .0014 10 0 711 . 1375 5 , 2 - .008 .45 .0000 .0 
3 
Wave ,oooc 20 0 1 204 ,4612 2 . 6 -.056 .35 , oooo ,0 
3 
External , oooo 30 0 1 478 ,9067 1 . 6 - .109 .26 .oooo .0 
3 
Tanks .oooo 40 0 1 393 1.2514 1. 1 -.147 . 17 . oooo .0 
J 
Bombs .oooo Slope Factors 
Stores . oooo Cl/Alpha (per radian) 1.9953 
Extra . oooo Cdl/Cl -2 . 6349 
Alpha Transition Zone 2 - 3 3 .021 
Camber .oooo Programmed Flap Setting a. 
Cdmin . 0196 Flap Type Single 42 . sq 
ft 
Mach 
Altitude 
.85 
30000. 
Parasite Drag Induced Drag 
Friction 
Sons 
Body 
2 
. 0107 
.0058 
Alpha 
. 0 
Cl 
000 
Cd 
.0196 
L/D 
. 0 
Cm 
,000 
e 
.00 
Cdtrim 
,0000 
Deltrim 
.0 
Wing . 0025 1 0 094 .0207 4 6 .001 .88 . 0000 ,C 
Strakes .0000 2 0 187 .0238 7 9 . 002 .88 .0000 .0 
H. Tail . 0013 3 0 277 ,0315 8 8 .002 .69 ,0000 .0 
V. Tail .0012 4 0 341 .0410 8 3 .001 .58 . oooo . 0 
3 
Canard . oooc 
in 0 407 .0518 7 9 . OOC .55 .0000 .0 
3 
Interference ,0014 10 0 72C .1408 5 1 -.011 .45 .oooo .0 
Wave . oooo 20 0 1 217 .4703 2 6 - . 063 .35 .oooo .0 
3 
External 
i 
. oooo 30 0 1 494 .9219 1 6 -.117 .26 .0000 .0 
Tanks .0000 40 0 1 405 1.3757 1 0 - .139 .15 .oooo .0 
4 
Bombs 
Stores 
Extra 
. oooo 
. oooo 
,0000 
Slope Factors 
Cl/Alpha (per radian) 2.0126 
Cdl/Cl"2 .6870 
Alpha Transition Zone 2-3 2.809 
Camber .0000 
Cdmin 
ft 
.0196 
Programmed Flap Setting 
Flap Type Single 
Nov 18 H 
15:07:52 F16-ACSYNT-OUT 
Mach 
Altitude 
. 90 
30000. 
Parasite Drag Induced Drag 
Friction 
Zone 
Body 
2 
, 0106 
.0057 
Alpha 
.0 
Cl 
000 
Cd 
.0203 
L/D 
.0 
Cm 
.000 
e 
.oo 
Cdtrim 
.0000 
Deltrim 
. 0 
Wing .0025 1 0 099 .0215 4 6 .001 . 89 .0000 .0 
Strakes 
2 , 0000 
2 0 196 ,0249 7 8 .001 . 89 .0000 .0 
H. Tail 
2 
.0013 3 0 290 . 0336 8 6 .001 .67 .0000 .0 
V. Tail 
2 
. 0012 4 0 349 .0427 S 2 .000 . 58 .0000 ,0 
Canard ,0000 5 0 416 , 0539 1 7 - . 002 .55 . oooo .0 
Interference 
2 
.0015 10 0 731 .1452 5 0 - .015 .45 . oooo .0 
Wave .0000 20 0 1 232 .4813 2 6 -.068 .35 ,0000 . 0 
J 
External 
, oooo 30 0 1 434 ,9 581 1 5 - . 124 . 23 .oooc .0 
Tanks .oooo 40 0 1 384 1.3440 1 0 - .160 . 15 . oooo . c 
4 
Bombs 
Stores 
Extra 
Camber 
.0000 
. 0000 
. oooo 
.0000 
Slope Factors 
Cl/Alpha (per radian) 
Cdl/Cl"2 
Alpha Transition Zone 2-3 
Programmed Flap Setting 
Cdmin 
ft 
. 0203 Flap Type Single 
1. 9830 
, 6907 
2 . 615 
0. 
42. sq. 
Mach = .95 
Altitude = 30000, 
Parasite Drag Induced Drag 
Friction 
Zone 
Body 
. 0105 
. 0057 
Alpha 
.0 
Cl 
.ooo 
Cd 
.02 66 
L/D 
.0 
Cm 
000 
e 
.oo 
Cdtrim 
.0000 
Deltrim 
.0 
wing .0024 1 0 104 .0279 3 7 000 .89 ,0000 .0 
Strakes .0000 2 0 .207 .0318 6 5 000 . 87 . oooo .0 
H. Tail .0012 3 0 289 .0409 7 1 - . 001 . 62 .0000 .0 
3 
V. Tail .0012 4 0 358 .0501 7 1 - . 002 .58 .0000 .0 
3 
Canard -> . 0000 5 0 426 .0618 6 9 -. 004 . 55 .oooo .0 
Interference .0008 10 0 744 . 1557 4 8 - . 018 .45 .oooo .0 
3 
Wave . 0052 20 0 1 237 .5382 2 3 -. 081 .32 .oooo .0 
4 
External ,000C 30 0 1 378 .9167 1 5 -, 145 .23 ,oooo .0 
Tanks . 0000 40 0 1 348 1.3001 1 0 - . 171 . 15 .oooo .0 
Bombs .0000 Slope Factors 
Stores 
Extra 
.0000 
. 0000 
Cl/Alpha (per radian) 1.9311 
Cdl/Cl~2 .7008 
Alpha Transition zone 2-3 2.436 
. 0000 
Cdmin 
+ ft 
.0266 
Programmed Flap Setting 
Flap Type Single 
Detailed Aerodynamics Output Camber 
F16 - ACS YNT- O UT 
QBtoilad Aerodynamics Output Kach - 1.05 
AIM trurte = JOOOO. 
CimLer .0000 
Ci ag 
Parasi 
Frietien 
Zone 
body 2 
Wiilg 
2 
3trakes 
2 
H. Tail 
3 
V. Tail 
3 
Canard 
3 
Inter-iV-rence 3 
Wav-¬ 
External 
4 
Tanj ; 
. 0103 
. o o 5 6 
. 0024 
. OOOC 
.0012 
. 0012 
. • 10 . 0005 
. om 
. oooo 
. oooo 
Induced 
Alpha 
.0 
1 . 0 
2.0 
3 . 0 
4 .0 
5 , 0 
10 . 0 
20 . C 
30 . 0 
40.0 
D:aci 
Cl . ooc 
, 114 
.225 
.280 
.352 
.422 
.756 
1 .227 
1.389 
1.379 
Cd 
. 0430 
.0445 
.0193 
. 0570 
.0666 
. 0787 
. 1781 
.54QB 
.9235 
1.3153 
L/D 
. 0 
2 . 6 
4.5 
Cm 
000 
. 007 
.015 
CdL: im Dultrim 
4.9 -.('21 
5.3 -.028 
5.4 -.031; 
4.2 -.084 
2.3 -.119 
1.5 -.173 
1.0 -.166 
00 
. 89 
.79 
. 59 
. 56 
53 
. 45 
.32 
.23 
.16 
. 00:50 
.0000 
.0000 
. oooo 
.0000 
,0000 
.oooo . oooo 
.oooc 
• :dn: 1 n .0421 
Prograiraned Flap Setting 
Flap Type Sinyj '•• 
Output tor Module i 
. r K * ............ X * * r * * 
ENGINE SCWAkY 
ENGINE DIAMETER = 4 .-I . :-KH 
ENGINE LJ7NGTH = 14.05 FEET 
ENGINE VtVlTGH7 = -1570.70 POUNDS 
SYPAS5 RATIO = .73 
ND OF ENGINES = 1 . 
DF.AC, REF AREA - 300.00 SQ FEL".' 
= PE«[:eNT CF ENGINE CORRECTED AIRFLOW 
THRUST • ENGINE THRUST (POtJrJtlS PER ENGINE) 
S; C - ENGINE SPECIFIC FUEL CONSUMPTION 
THRUSTU= THBDST ENGINE IN LBS, W/O IHSTAL DRAG CORR 
SFCU = SVC, 1/HR, W/O INSTALLATION DRAG CORE. 
CDINS - TOT INSTALLAT1' 4 DRAG f.JBF : :•.!'. A/C (SWING REF) 
,00 DO Slope Factors MACH ALT PWCC THRUST THRUSTU SFC SFCU CDINS 
Stores . 0000 Cl/Alpha (per I vidian) 1 -97EF 
£xtl n 
. oooo Cdl/CI "2 .6668 
Alphd TrariB it Ion Zone 2- 3 2 .111 .000 0 . 100 . 17389. 0 . 857 .000 . 0000 
Ce. : .oooo Pre Flap Setting 0 . i1 8 . 16158, • . 841 .000 .0000 
96 . • r>. 0. . 0OD .aoor 
cdmin . 04": n Flap Type Single 42 . sq. 74 , IIB14. 0. 778 . ooo .oooo 4 
£t 92 . 9600. 0. 764 .000 .0000 
90 . 7235. o. tin . 00.7 . oooo 
Mach 1.2G 88, 43
 63 . 
0 . 974 . 000 .oooo A j i.i i
 jde 
= J0000. 
Parasi te Drag Induced Drag .450 ioooo. ioo. 12635. 0. 977 . 000 .oooc 
Frlct idn . oioc Aip If! Cl Cd L/D Cm e Cdtrim Deltrim o,-;. 11018. o. . 000 
+ Zone !7t . 9355. D . 927 .000 .oooo 
Body . 0054 0 . 000 0421 C 000 . 00 '•OOO 0 74 . 7
 1 6 . 
0. 916 .ooo .0000 4 
2 92 . 6054. 0 . 931 .0000 
W j ng . 0023 1 0 . 117 0437 2 . 7 -.009 o , oooo .0 90. 4 2 2 2, 0. i 011 . 1' 0 0 .0000 4 
2 88 . 2381 . 0, i 167 .ooo 0005 
5trakes .000 0 2 c . 232 0505 4 . 6 -.019 . 68 oooo .0 3 H. Tail . 0012 3 0 . 305 0594 5. 1 
- . 02 8 .57 oooo . 0 .7 50 
20000. 100 . 10456. 0. i 
0 00 . 000 . DO00 4 3 98 . 5019 . 0. 972 .ooo . oooo V. Tail .0011 4 0 . 383 0709 5. 4 -.038 . 54 oooo .0 96. 76/i . 0 951 .ooo ,0»00 
4 3 94. 1258 . 0. .• 1 . ooc . BOD0 CanaiA .oooo S 0 . 459 0B55 5 . 4 - . 048 . 52 oooo .0 92 . 4167. 0 . 951 .000 .0000 4 3 90. 3613 . o. i 013 ooo . oooo 
Interference .0004 10 0 . 824 2033 4 . 1 - . 10B .45 ooo
 0 
.0 . 219/2. 0. i 243 . ooo . oooo 4 3 
it. 537 . 0. 3 547 . oo .c-ooo 
H'ave . 0180 20 0 1,3
 64 
6012 2 . 3 -.210 .35 oooo .0 
fixtemi) . oooo iO 0 1 . 547 1 0236 1 , 5 -.27C .26 oooo . 0 .900 30000. 100. 7772 . 0 . 980 .000 . oouo 4 4 9B . 6713 . o. 953 .ooo . 01 i0 Tanks .oooo 40 0 1 . 833 1 5667 1 . 2 - .355 . 23 :••}•• 0 .0 9G. 5088. 0. 931 . i .oooo 
4 6 94. 4690. o. 920 j . .oooo Li . . . oooo Slppo Fact,. r^ 91. 5V06. o. 927 .000 .oooo Stores , oooo Cl/Alpha (per radian) 7 . 6251 90. ' • 0. 977 .aoo .oooo 
F-xt ra . oooo CA1 KX y .4519 A3 1713 . 0. L 154 ooo .0000 Al-!ia Trsnsi tjran Zone 2-3 1 . 673 ii. 59 3 . 0. ; 306 .000 .0000 
15:07:52 F16-ACSYNT-OUT 
Avionics 2414. 1095. 6 82 i oo Yes 
Instrumentation 107 . 49 . 30 i 00 Yes 
10000. 100. 6934. 0. 1 008 .000 .0000 De-ice & Air Cond 267. 121. 75 I 00 Yes 
98. 6042 , 0. 981 .000 ,0000 Auxiliary Gear 172. 78. 49 Yes 
96. 5137 . 0. 956 . 000 .0000 Furnish li Eqpt 312. 142. 88 i 00 Yes 
94 . 4264 . 0. 939 , 000 .0000 Flight Controls 730. 331 . 2 06 i 00 Yes 
92 , 3417 . 0 . 934 .000 ,0000 
90. 2585, 0. 957 .000 .0000 Empty Weight 17763. 8057. 50 19 
88 . 1760 . 0, 1 048 . 000 . oooo 
B6 . 911. 0. 1 415 .000 . oooo Operating Items 0, 0. 00 No 
Flight Crew ( 1) 215. 98. 61 Yes 
Crew Baggage and Provisions 0. 0. 00 No 
AFTERBURNEF OR DUCTBURNER (OR BOTH) LIT Unusable Fuel and Oil 74 . 34 . 21 No 
Operating Weight Empty 18052. 8188. 51 01 
50000. 100. 12225. 0 . 2 376 .ooo .0000 
100 . 11885. 0 . 2 321 ,000 .0000 Fuel 13658. 6195. 38 59 
100. 11544. 0. 2 266 .000 , oooo 
100. 11201. 0. 2 210 . ooo .oooo Payload 3678 . 1669 , 10 39 No 
100. 10856. 0. 2 154 .000 .oooo Armament 808 . 367 . 2 28 Yes 
100. 10508. 0 . 2 097 .OOC .0000 Ammuni ti on 103. 47 . 29 Yes 
100 . 10159, 0. 2 039 .ooo .0000 Missiles 1066. 484 . 3 01 Yes 
100 . 9806 . 0. 1 980 .000 .0000 Bombs 172 . 78 . 49 Yes 
100, 9450 . 0. 1 920 .000 ,0000 External Tanks 1529 . 694 . 4 32 Yes 
100. 9092 . 0. 1 859 .ooo .0000 Adv Weapons 1 0. 0. 00 No 
loo. 8729 . 0 . 1 797 .000 .oooo Adv Weapons 2 0 . 0. OO Nc 
100 . 8363. 0 . 1 733 .000 .0000 
100 . 7992 . 0. 1 667 ,000 .0000 Calculated Weight 35388. 16052. 100 00 No 
100. 7616. 0. 1 598 . 000 , oooo 
100. 7236 . 0. 1 528 .000 .oooo Estimated weight 35388. 16052. 
SEA-LEVEL STATIC THRUST ' 
SEA-LEVEL SFC 
Output for Module # 6 
24850. 
3 . 140 
(MAX) 
Weight Statement - Fighter 
QMAX: 
Design Load Factor: 
Ultimate Load Factor: 
Structure and Material: 
wing Equation: 
Body Equation: 
Component 
1900 . 
9 . 00 
13 .50 
Aluminum Skin, Stringer 
Delta Wing Equation 
Sanders Equation 
Pounds Kilograms Percent Slope Tech Fixed 
Airframe Structure 8275. 3754 . 23 38 Nc 
Wing 2096. 951. 5 92 1 00 1 00 Yes 
Fuselage 3624 . 1644. 10 24 1 00 1 00 Yes 
Horizontal Tail ( Low] 498 . 226 . 1 41 I 00 1 00 Yes 
Vertical Tail 376. 171 . 1 06 1 00 1 00 Yes 
Nacelles 689 , 312 . 1 95 1 00 1 oc Yes 
Landing Gear 992 , 450. 2 80 1 00 1 00 Yes 
Propulsion 4489. 2036. 12 69 No 
Engines ( 1) 3911. 1774 . 11 05 1 00 1 00 Yes 
Fuel System 578. 262. 1 63 1 00 1 00 Yes 
Fixed Equipment 4998 , 2267 . 14 12 1 00 No 
Hyd & Pneumatic 311 . 141 . 88 1 oc Yes 
Electrical 686 . 311 . 1 94 1 00 Yes 
percent Error .00 
Nov 18 96 
15:07:32 Fl 6-ACS YNT-OUT 
Output for Module t 11 
1 SUMMARY ACSYNT OUTPUT NASA, AMES RESEARCH CENTER 
ENGLISH UNITS -
***** GENERAL DYNAMICS F-16C FIGHTER - COMBAT AIR PATROL **************** 
DISTANCES IN FEET 
WEIGHTS IN LBS. 
GENERAL FUSELAGE WING HTAIL VTAIL 
FORCES IN LBS. 
PRESSURES IN LBS/FT**2 
WG 35388. LENGTH 47 .6 AREA 300.0 63.7 54.8 
W/S 118.0 DIAMETER 3 .8 WETTED AREA 333 . 1 115.3 116.9 
T/W .70 VOLUME 473 ,2 SPAN 30 .0 11.6 8 . 4 
N(Z) ULT 13.5 WETTED AREA 758 . 2 L.E. SWEEP 40,0 40.0 47 .5 
CREW 1 , FINENESS RATIO 12 . 5 C/4 SWEEP 32 .2 32 ,3 43 .2 
PASENGERS 0. ASPECT RATIO 3 .00 2.11 1 .29 
TAPER RATIO ,23 . 39 ,44 
ENGINE WEIGHTS T/C ROOT .04 ,06 .05 
T/C TIP .04 ,04 .03 
NUMBER 1. W WG ROOT CHORD 16.3 7.9 9.1 
LENGTH 14.1 STRUCT. 8275 23 .4 TIP CHORD 3 .7 3.1 4 . 0 
DIAM. 4.4 PROFUL. 4489 12 .7 M.A. CHORD 11.3 5.8 6.8 
WEIGHT 4570.7 FIX . EQ . 4998 14 .1 LOC. OF L.E. 18.2 38.4 36.1 
TSLS 24850, FUEL 13732 38 . 8 
SFCSLS 3.14 PAYLOAD 3678 10 .4 
MISSION SUMMARY 
PHASE MACH ALT FUEL TIME DIST L/D THRUST SFC Q 
TAKEOFF . 00 0 . 653 . 1 0 4706 6 
CLIMB .91 10000. 165. 6 5 5 5 95 14918 9 1 ,027 837 8 
CLIMB .91 20000, 163 . S 7 0 7 92 11431 2 1 .014 558 2 
CLIMB 1 . 10 32500. 299 . 2 0 19 2 4 64 8842 1 1 .008 478 7 
CRUISE . 87 33528. 1929 . 30 7 258 8 8 02 4085 CO .899 286 1 
LOITER . 80 28500. 7157 . 120 0 949 2 8 23 3915 5 .914 301 8 
COMBAT .90 10000. 412 . 1 0 9 6 6 99 17716 6 1 ,394 825 3 
COMBAT .90 10000, 211. 1 0 9 6 8 77 12406 8 1 .021 825 3 
CLIMB 1.30 44500, 319 . 2 6 24 1 5 68 5910 9 1 .013 372 9 
CRUISE .87 45315. 1215 , 34 9 2 90 5 8 94 2298 6 .886 161 5 
LOITER .40 1. 1350. 20 0 88 2 12 52 1610 6 2 .515 237 0 
LANDING 8069 7 
Block Time 
Block Range = 1661.7 nro 
3.677 hr (without air and ground manusver allowances) 
COMBAT PHASES 
MACH ALT PS1G NZS CLS CDS ALS NZI PSI CLI CDI ALI CBE 
.90 10000. 1014. 6.9 .498 .0711 6.2 7.5 -191. .731 .1452 10.0 60834. 
.90 10000. 1251. 8.2 .438 .0499 5.3 8.5 -126. .731 .1370 10.0 75070. 
Appendix G Page 60 
Appendix G. F16C FLOPS Input & Output File 
Nov IS 96 
15:07:53 F16-FLOPS-IN 
PARA 
£16c Air Superiority Mission, 2AIM-9, 2AIM-120, External Fuel 
SOPTION 
I0PT=1, 
IFITE=1, 
ICOST=0, 
IANAL=3 , 
IENG=1, 
SEND 
SWTIN 
ULF=13.5, 
VHMO=2.4, 
MYWTS=0, 
HYTJPR=3000 . , 
DIH=0.0, 
FLAPR=0.227, 
GLOV=0., 
VARSWP=0,, 
FCOMP=0.2, 
FAERT-0., 
FSTRT-0 . , 
XL=44.1, 
WF=4.9, 
DF-3.46, 
XLP=0.0, 
N£W=0, 
NEF=1, 
THRSO=248S0., 
HENG=3911,, 
FULWMX=1144 . , 
NTANK=5, 
FULFMX=5831., 
FULAUX = 6760., 
FRWI=2096., 
FRKT=498., 
FRVT=376., 
FRFU=3 624. , 
FRLGM=992. , 
FRNA=689., 
WFSYS=578., 
WHYD=311 . , 
WIN=107., 
WELEC=686 . , 
WARM=808.5, 
WFURN=312., 
WAC=267., 
WCON=172,, 
WFLCRB=215., 
WAUXT=1701. , 
WSRV=I02.5, 
FRSC=730., 
XNAC=31., 
DNAC=2.81, 
EEXP=0.6, 
NPF=0, 
NPT=0, 
CARGOW=0. , 
CARGOW=1066. , 
CARGOF=0. , 
WAVONC=243 8., 
SVT=54.75, 
SWPVT=42 . 93 , 
ARVT=1.2 94, 
TRVT-.437, 
TCVT=.04S, 
SHT=63.7, 
ARHT=2.114, 
SWPHT=32.18, 
TRHT=.390, 
TCHT=.051, 
HHT=0.0, 
XMLG=49.9, 
XNLG=39.0, 
SEND 
SCONFIN 
DESRNG=580.6, 
GW=32974. ,0.0, 
AR-3.0.0.,2.0,4 .0, 
SW=300.0,0.,400.,600., 
TR=0.2275,0.0, 
SWEEP=30.0,0.0, 
TCA=.04,0.0, 
THRUST=24850.0,0.0,20000.0,35000.0, 
VCMN=0.8, 
CH=50000., 
SEND 
SAER1N 
MYAERO=l, 
MAVE=1 , 
SEND 
SENGDIN 
IGENEN=-1, 
EIFILE='GE12 9.instal.engine.txt', 
NGPRT-1, 
IDLE=0, 
IXTRAP=1, 
IFILL=3, 
MAXCR=2 , 
IGEO=0, 
SEND 
SMISSIN 
INDR=0, 
IFLAG=2 , 
IRW=1, 
IATA=0, 
STMA(1,11=0.3,STMA (2,1)=0.9.STMA(3,1)=1.0,STMA< 4,1) = 1. 4 , 
STMA(1,2)=0.3,STMA(2,2)=0.9,STMA(3,21=1.2,STMA (4,2)=1.6, 
STMA(1,3)=0.3,STMA(2,31=0.9,STMA(3,3)=0.95,STMA(4,3)=1.4, 
CDST (1,1) = .0058, CDST (2,1) =.0062, CDST, 3,1) =".0138, CDST (4,1) = .02 62, 
CDST(1,2 I *.0016,COST(2,2) = .0016,CDST(3,2) = .0047,CDST(4,2) = .0053, 
CDSTfl,3)=-.0007,CDST(2,3)—.0008,CDST(3,3)=-.0008,CDST(4,3)--.0012, 
ISTCL[1)=2, ISTCL(2)=3, 
ISTCR(1>=1, ISTCR(2)=3, 1STCR(3)=3, ISTCR(4)=3, ISTCR(5)=3, 
PAYLOD=3654. , 
TAXOTM=6.5, TAKOTM=0.5, TAXITM=0., ITTFF=1, 
NCLIMB=2, 
CLMMIN(l)=0.3,CLMMAX(1)-0.9,CLAMIN(11=0.0,CLAMAX (1)=32500,, 
CLMMIN(2)-0.3,CLMMAX(2)=0.9,CLAMIN(2)=10000.,CLAMAX(21=50000. , 
NINCL(1)=20, NTNCL(2)=20, 
FWE(11=-0.001, FWF(2)=-0.001, 
NCRCL(1)=1, NCRCL(2)*=4, 
CLDCDI11=0.0, CLDCDI2)=0,0, 
IPPCL(1)=4, IPPCL(2)=4, 
NO(11=0, NO(21=0, 
IFAACL=0, 
NODIVE=l, 
NCROSE=5, 
IOC(1)=0, IOC<2)=0, IOC(3)=4, IOC(4)=0, IOC(5)=0, 
CRMACH=0,9,0.9,0.9,0.9,0.8, 
CRALT=50000.,50000.,50000.,50000.,0.0, 
CRDCD=0.00,0.00,0.00,0.00,0.00, 
CRMMIN=0.70,0.70,0.3,0.7,0.3, 
CRCLMX=1.0,1.0,1,0,1.0,1.0, 
HPMIN=30000.,30000.,0.0.35000.,0.0, 
FH 
IRS=2, 
RESRFU=0.00, 
HPMIN= 200. 
ivs=o, 
NPCON= 5, 
FCDO=l • 0, 
FCDI=1 0, 
SEND 
START 
CLIMB 1 
CRUISE 1 
HOLD 3 120. 
RELEASE 1529 , 
ACCEL 2 0 .9 
TURN 2 1 360. 
TURN 2 1 360. 
TURN 2 1 360 . 
TURN 2 1 3 60. 
TURN 2 1 3 60. 
TURN 2 1 110. 
RELEASE U6S.5 
CLIMB 2 
CRUISE 4 
HOLD 5 20 . 
DESCENT 
END 
250. 
0.7 
0.9 
0.9 
0. 
10000 , 
10000. 
10000. 
10000. 
10000. 
10000. 
ioooo. 
10000. 
270 . 
SPCONIN 
CONALT=3 0000.0, 
CONFMiO.4, 
SEND 
SPCONIN 
CONALT=30000 
CONFM=0.4, 
SEND 
SPCONIN 
CONALT=30000.0 
CONKCH= 
ICONTP=16, 
0, CONMCH= 
ICONTP=8, 
0.8, CONPC=l.0, 
CONAUX^l.4, 
NEO=l, IC5TDG=3, 
0.9, CONPC=1.0, NEO=l, ICSTDG=3, 
C0NMCH=0.9, 
CONFM=0.4, 
SEND 
SPCONIN 
CONALT=30000 
CONFM=0. 4, 
SEND 
$ PCONIN 
CONALT=3O000 . 
ICONSG=4, 
SEND 
24 18 
ICONTP=12, 
0, CONMCH= 
ICONTP=9, 
0.9, 
0, CONMCH= 
ICONTP=8 
1-2, 
CONPC=1.0, NEO=l, ICSTDG=3, 
CONPC=1.0, NEO=l, ICSTDG=3, 
CONPC=1.0, NEO=l, ICSTDG=2, 
0 ooooo 0 20000 0 30000 0 40000 0 .50000 c 60000 0 70000 0 80000 0 85000 0 90000 
0 9500C 1 ooooc 1 05000 1 10000 1 20000 1 30000 1 40000 1 50000 1 60000 1 70000 
1 80000 1 90000 2 ooooo 2 10000 
0 ooooo 0 05000 0 10000 0 15O00 0 20000 0 30000 0 40000 0 50000 0 60000 0 70000 
0 80000 0 90000 1 ooooo 1 10000 1 20OO0 1 30000 1 40000 1 50000 
0 ooooo 0 ooooo 0 00040 0 00140 0 00310 0 00810 0 01650 0 02850 0 04470 0 06690 
0 09410 0 12030 0 13370 0 1671C 0 21050 0 26300 0 33900 0 41600 0 ooooo 0 ooooo 
0 OO050 0 00150 0 00330 0 00860 0 01700 0 02830 0 04280 0 06070 0 08360 0 11100 
0 14140 0 17890 0 22460 0 28390 c 36400 D 45790 0 ooooo 0 ooooo 0 00050 0 00150 
0 0O330 0 00880 0 01710 0 02820 0 04210 0 05790 0 08010 0 10780 0 14520 C 18510 
0 23200 0 29580 0 37650 0 47950 0 ooooo 0 OOOOO 0 0OO60 0 00170 0 00340 0 00900 
0 01730 0 02820 0 04160 0 05630 0 07800 0 10620 0 14910 0 19150 0 24140 0 30740 
0 38990 0 5O190 0 ooooo 0 ooooo 0 0O05C 0 00160 0 00340 0 0090C 0 01740 0 02810 
0 04120 0 O4600 0 07620 0 10590 0 15330 0 19820 0 25160 0 32010 0 40410 0 52560 
0 ooooo 0 OOOOC 0 00050 0 00150 0 00340 0 00900 0 01730 0 02800 0 04110 0 05650 
0 0758C 0 1O810 0 15860 0 20530 0 26260 0 33300 0 41920 0 55040 0 00000- 0 00010 
0 00040 0 00150 0 00340 0 00900 0 01720 0 02890 0 04150 0 05810 0 07960 0 11250 
0 16090 0 21170 0 27380 0 34480 0 43130 0 57030 0 ooooo 0 00010 0 00060 0 00170 
0 00350 0 00890 0 0171C 0 02 800 0 04230 0 06030 0 03440 0 11830 0 16320 0 21660 
3 28580 0 36210 0 44640 0 59120 0 ooooo 0 00020 0 00070 0 00190 0 00360 0 00900 
0 .01710 3 ,02810 0 .04270 0 .06130 0 ,08710 0 12240 C .16770 0 .22140 0 .29630 0 .37720 
0 .45920 3 .61220 0 ,00000 3 .00020 0 .00080 0 00230 0 .00440 0 01060 0 01860 0 .0298C 
0 .04540 0 ,06560 0 .0920C 0 .13040 0 . 17950 0 24440 0 .32020 0 41000 0 51460 0 .72820 
0 .00000 0 .00060 0 .00160 0 ,00320 0 .00530 0 O1180 0 .02240 0 03690 0 O5430 0 ,07390 
c .10150 0 .13870 0 .19940 a .27140 0 .33850 9 .99000 9 .99000 9 .990OC 0 . OOOOO 0 00010 
0 .0012C 0 .0031C 0 .00590 0 .0145C 0 0262C 0 .04340 0 .06560 0 .08800 0 .12360 0 17620 
0 .23580 0 .28620 0 .35370 9 ,99000 9 .99000 9 99000 0 .00000 0 00040 0 00160 0 .00330 
0 .00620 0 ,013 80 0 .02730 c .04560 0 ,07030 C 09580 0 13950 0 19100 C 24950 0 .31000 
0 .37300 9 .99000 9 ,99000 9 .99000 0 .00000 0 00040 0 . 00160 0 OO330 0 00650 0 .01540 
0 .02830 0 .04860 0 .07760 0 ,11250 0 15050 0 19940 0 ,25460 0 31490 0 38390 9 99000 
9 .99000 9 ,99000 0 ,00000 0 ooooo 0 00120 0 00340 0 .00720 0 O1740 0 03110 0 05570 
0 .08890 0 .13250 0 , 16670 0 21240 0 26000 0 3O980 0 .39630 9 99000 9 99O00 9 99000 
0 .00000 0 .00060 0 .00200 3 .00460 0 .00900 0 01910 0 03630 3 06280 0 09760 0 .13760 
0 .1B16C 0 25220 0 .33350 9 .99000 9 99O0C 9 99000 9 99OO0 9 9900C 0 ooooo 0 .00060 
0 .00220 0 00590 0 01060 0 02200 0 04330 0 06980 0 .1065Q 0 15O70 0 20340 0 29930 
0 ,38530 9 .99000 9 .99000 9 99000 9 99000 9 99000 0 .00000 0 00060 0 00280 0 00650 
0 .01210 0 .02 640 0 04970 0 07730 0 11790 0 16710 0 .22820 0 32260 0 4078C 9 99000 
5 .99000 9 99000 9 99000 9 99000 0 ooooo 0 O0060 c 00280 0 00670 0 O1280 0 03010 
0 05530 C 08400 0 13270 0 18820 0 25780 0 33420 0 41830 9 99000 3 99000 3 99000 
s 99000 9 99000 0 OOOOO 0 00070 0 00290 0 00690 0 01320 0 O3290 0 06140 0 09330 
9 99000 9 99000 9 99000 9 99000 9 99000 9 99000 9 99000 9 99000 9 99000 9 99000 
0 .00000 0 00070 0 00300 0 OO720 0 01370 0 03530 0 06760 0 10440 9 990OC 9 9900C 
9 99000 9 99000 9 99000 9 99000 9 99000 9 99OO0 9 990O0 9 9900C 0 OOOOC 0 0OO60 
0 00290 0 00720 0 01420 0 03790 0 07340 0 11800 9 99000 9 99000 9 99000 9 99000 
9 99000 9 99000 9 99000 9 99000 9 99000 9 99000 0 OOOOO 0 00050 0 00280 0 00720 
0 01480 0 04030 0 07930 0 13330 9 99OO0 9 99000 9 99000 9 99000 9 990OO 9 99000 
9 99000 9 99000 9 99000 9 99000 0 OOOOO 0 00070 0 00300 0 00770 0 Ol 400 0 04320 
0 08600 0 14950 9 99000 9 99000 9 99000 9 99000 9 99000 9 99000 9 99000 9 99000 
9.99000 
13 23 
9 99000 
0. 5000. 10000, 15000. 20000. 25000. 3 0000. 35000, 4000O. 45000. 
50000. 55000. 60000. 
0 OOOOO 0 20000 0 3OOO0 0 40000 0 50000 0 60000 0 70000 0 80000 0 85000 0 90000 
0 95000 1 OOOOO 1 05000 1 IOOOO 1 20000 1 30000 1 40000 1 50000 1 60000 1 70000 
1 80000 1 90000 2 00000 
0 01853 0 01743 0 01719 0 01689 0 01677 0 01641 0 01645 D 01703 0 01731 0 01747 
0 01763 0 02198 0 02222 0 02116 0 02221 0 02040 0 02023 0 02085 0 02269 0 02430 
0 02540 0 02436 0 02445 0 O1880 0 01770 0 01744 0 01713 0 017OC 0 016SS 0 01645 
0 01703 0 01731 0 01747 0 01763 0 02198 0 02222 0 02116 0 02221 0 02040 0 02023 
0 02085 0 02269 0 02430 0 02540 0 02436 0 02445 0 01910 0 01800 0 01771 C 01739 
0 01724 0 01678 0 01662 0 01705 0 01731 0 01747 0 01763 0 02198 0 02222 0 02116 
0 02221 0 O2040 0 02023 0 02085 0 02269 0 02430 0 02540 0 02436 0 02445 a 01941 
0 01831 0 01800 0 01766 0 01750 0 01703 0 01686 0 01728 0 01749 0 01760 0 01771 
0 02202 0 02223 0 02116 0 02221 0 02040 0 02023 0 02085 0 02269 0 02430 0 02540 
0 02436 0 02445 0 01975 0 01865 0 01831 0 01795 0 01778 0 01730 0 01712 0 01754 
0 01774 0 01785 0 01796 0 02226 0 02247 0 02137 0 02238 0 02053 0 02034 0 02095 
0 02279 0 02440 0 02551 0 02449 0 02462 0 02011 0 01901 0 01864 0 01826 0 01808 
0 01759 0 01740 0 01781 D 01801 0 01811 0 01822 0 02252 0 02272 0 02163 0 02263 
0 02077 0 02059 0 02119 0 02303 0 02464 0 02574 0 02472 0 02485 0 02050 0 01940 
0 01900 0 01860 0 01840 0 0179C 0 01770 0 01810 0 01830 0 01840 0 01850 0 02280 
0 02300 0 02190 0 02290 0 02104 0 02085 0 02145 0 02328 0 02489 0 02599 0 02497 
0 02509 0 02092 0 01982 0 01939 0 01896 0 01875 0 01823 0 01802 0 01841 0 01861 
0 01871 0 01880 0 02310 0 02330 0 02220 0 02319 0 02133 0 02113 0 02173 0 02355 
0 02516 0 02626 0 02524 0 02535 0 02149 0 02039 0 01991 0 01946 0 01922 0 01869 
0 01846 0 01884 0 01903 0 01912 0 01922 0 02351 0 0237C 0 02260 0 023 58 0 02171 
0 021S1 0 02210 0 02393 0 02553 0 02662 0 02560 0 02571 0 02213 0 02103 0 02O50 
0 02001 0 01974 0 01919 0 01895 0 01932 0 01950 0 01959 0 01968 0 02396 0 02415 
0 02304 0. 02402 0 02214 0 02194 0 02252 0 02434 0 02594 0 02703 0 02599 0 02610 
0 02281 0 02171 0 02111 0 02059 0 02029 0 01972 0 01946 0 01982 0 02000 0 02008 
0 02016 0 02444 0 02462 0. 02351 0 02448 0 02260 0 02238 0 02296 0 02477 0 02636 
0 02745 0 02641 0 02652 0. 023 53 0 02243 0 02176 0 02120 0 02088 0 02028 0 02O01 
0. 02034 0. 02051 0. 02059 0. 02066 0 02494 0 02512 0 02400 0 02496 0 02307 0 02285 
0. 02342 0 . 02523 0. 02681 0 02789 0 02685 0 02695 0 02428 0 02318 0 02245 0 02184 
0, 02149 0 . 02087 0. 02058 0 02090 0 02106 0 02113 0 02120 0 02547 0 02564 0 02452 
0 02547 0. 02357 0 02334 0. 02391 0 02571 0 02729 0 02836 0 02731 0 02741 
0. OOOOO 0. OOOOO 0. OOOOC 0 . ooooo 0 ooooo 0. 00050 0 00100 0 00130 0 00150 0 00200 
0. 01000 0 . 02000 0, 02200 0 . 02300 0. 02160 0 02296 0 02345 0 02345 0 02292 0 02181 
Nov 18 96 
15:07:53 F16-FLOPS-IN 
0.02081 0.02153 0.02081 
((TITLE, BEGIN INPUT DATA ECHO 
f!6c Air Superiority Mission, 2AIM-9, 2AIM-120, External Fuel 
* NAMELIST $WTIN 
GEOMETRIC, WEIGHT, BALANCE AND INERTIA DATA 
DESCRIPTION NAME VALUE DIMENSIONS 
MAX OPER MACH NUMBER VMMO 2 .4000 
ULTIMATE LOAD FACTOR ULF 13.5000 
REF WEIGHT NUMBER NWREP 39 
CG REFERENCE LENGTH CGREFL 529.2 IN 
X FOR START OF CGREFL CGREFX .0 IN 
SWITCH TO COMPUTE WEIGHTS MYWTS 0 
DESIGN GROSS WT. (RATIO) DGW 1 .000 
HYDRAULIC SYSTEM PRESSURE HYDPR 3000. 
WING DATA 
DIHEDRAL(POSITIVE) 
GLOVE AND BAT AREA 
SPAN 
DIH 
GLOV 
SPAN 
CONTROL SURFACE AREA RATIO FLAPR 
FRACTION OF COMPOSITES FCOMP 
AEROELASTIC TAILORING fALT FAERT 
STRUT BRACING FACTOR FSTRT 
VARIABLE SWEEP FACTOR VARSWP 
, 000 
.00 
30 .00 
.2270 
.2000 
. oooo 
,0000 
.0000 
DEG 
SQ FT 
FT 
HORIZONTAL TAIL DATA 
AREA SHT 
1/4 CHORD SWEEP ANGLE SWPHT 
ASPECT RATIO ARH
TAPER RATIO TRHT 
T/C TCH
LOCATION ON VERTICAL TAIL HHT 
S3 .70 
32.IS 
2.11 
,3900 
.0510 
.0000 
SQ FT 
DEG 
VERTICAL TAIL DATA 
NUMBER OF VERTICAL TAILS NVERT 1 
AREA SVT 54.75 
1/4 CHORD SWEEP ANGLE SWPVT 42.93 
ASPECT RATIO ARVT 1.2940 
TAPER RATIO TRVT .4370 
T/C TCVT .04 50 
SQ FT 
DEG 
FUSELAGE DATA 
NUMBER OF FUSELAGES NFUSE 
TOTAL LENGTH XL 
MAXIMUM WIDTH WF 
MAXIMUM DEPTH D
CARGO AIRCRAFT FACTOR CARGF 
PASSENGER COMPART LENGTH XLP 
1 
44.10 
4 .90 
3,46 
.0000 
-8.52 
FT FT FT 
FT {CALC) 
LANDING GEAR DATA 
LENGTH OF MAIN GEAR XMLG 4 9.90 
LENGTH OF NOSE GEAR XNLG 39.00 
DESIGN LANDING WEIGHT WLDG 31538.1 
SET WLDG TO END OF DESCENT MLDWT 0 
CARRIER BASED AIRCRAFT CARBAS .00 
IN IN LBF 
PROPULSION SYSTEM DATA 
NUMBER OF ENGINES ON WING NEW 0 
NUMBER OF ENGINES ON FUSE NEF 1 
BASELINE ENGINE THRUST THRSO 24850.0 
BASELINE ENGINE WEIGHT WENG 3911.0 
LBF 
LBF 
-OUT 
WEIGHT SCALING PARAMETER EEXP ,60000 
BASELINE INLET WEIGHT WINL .0 LBF 
INLET WT SCALING EXPONENT El ML 1.00000 
BASELINE NOZZLE WEIGHT WNOZ .0 LBF 
NOZZLE WT SCALING EXPONENT ENOZ 1.00000 
BASELINE NACELLE LENGTH XNAC 31.00 FT 
BASELINE NACELLE DIAMETER DNAC 2 . 81 FT 
FUEL CAPACITY OF WING FULWMX 1144.0 LBM 
(FUEL CAPACITY FACTOR FWMAX 11.229) 
FUEL CAPACITY OF FUSELAGE FULFMX 5831.0 LBM 
ADJUST FUSE FUEL CAPACITY IFUFU 0 
AUXIL TANK FUEL CAPACITY FULAUX 6760.0 LBM 
NUMBER OF FUEL TANKS NTANK 5 
ADDED MISC PROP SYSTEM WT WPMISC .000 LBF 
CREW AND PAYLOAD DATA 
FIRST CLASS PASSENGERS NPF 0 
TOURIST PASSENGERS NPT
STEWARDESSES NSTU -1 
GALLEY CREW NGALC
FLIGHT CREW NFLCR -1 
WEIGHT PER PASSENGER WPPASS 165.0 
BAGGAGE PER PASSENGER BPP 35,
CARGO IN WING CARGOW 1066.0 
CARGO IN FUSELAGE CARGOF .
LBF 
LBF 
LBF 
LBF 
OVERRIDE PARAMETERS FOR WEIGHTS 
WING - TOTAL FRWI 2096 0000 
WING WEIGHT FIRST TERM FRWI1 1 0000 
WING WEIGHT SECOND TERM FRWI 2 1 OOOC 
WING WEIGHT THIRD TERM FRWI 3 1 0000 
HORIZONTAL TAIL FRHT 498 oooo 
VERTICAL TAIL FRVT 376 oooo 
WING VERTICAL FIN FRFIN 1 oooo 
CANARD FRCAN 1 oooo 
FUSELAGE FRFU 3624 oooo 
NOSE LANDING GEAR FRLGN 1 oooo 
MAIN LANDING GEAR FRLGM 992 oooo 
NACELLES - TOTAL OR FRNA 689 oooo 
AIR INDUCTION SYSTEM 
THRUST REVERSERS - TOTAL WTHR oooo 
MISC PROPULSION SYSTEMS WPMSC 1 oooo 
FUEL SYSTEM WFSYS 578 oooo 
SURFACE CONTROLS FRSC 730 oooo 
AUXILIARY POWER UNIT WAPU 1 oooo 
INSTRUMENT GROUP WIN 107 oooo 
HYDRAULICS GROUP WHYD 311 0000 
ELECTRICAL GROUP W2LEC 686 oooo 
AVIONICS GROUP WAVONC 2438 oooo 
ARMAMENT GROUP WARM 808 500C 
FURNISHINGS GROUP WFURN 312 oooo 
AIR CONDITIONING GROUP WAC 2 67 oooo 
ANTI-ICING GROUP OR WAI 1 oooo 
AUXILIARY GEAR 
UNUSABLE FUEL WUF 1 oooo 
ENGINE OIL WOIL 1 oooo 
PASSENGER SERVICE OR AMMO WSRV 102 5000 
AND NONFIXED WEAPONS 
CARGO AND BAGGAGE CONTAIN, WCON 172 oooo 
OR MISCELL. USEFUL LOAD 
AUXILIARY FUEL TANKS WAUXT 1701 oooo 
FLIGHT CREW AND BAGGAGE WFLCRB 215 oooo 
CABIN CREW AND BAGGAGE WSTUAB 1 oooo 
HORIZONTAL CENTER OF GRAVITY DATA 
WING CGW 0 IN 
Nov 18 96 
I5:07:M 
HORIZONTAL TAIL CGHT .0 IN 
VERTICAL TAIL CGVT .0 IN 
WING VERTICAL FINS CGFIN . 0 IN 
CANARD CGCAN . 0 IN 
FUSELAGE CGF ,0 IN 
NOSE LANDING GEAR CGLGN .0 IN 
MAIN LANDING GEAR CGLGM . 0 IN 
TWO FORWARD ENGINES CGEF . 0 IN 
ONE OR TWO AFT ENGINES CGEA .0 IN 
AUXILIARY POWER UNIT CGAP .0 IN 
AVIONICS GROUP CGAV . 0 IN 
ARMAMENT GROUP CGARM .0 IN 
FLIGHT CREW CGCR .0 IN 
PASSENGERS CGP .0 IN 
CARGO/EXT STORES IN WING CGCW .0 IN 
CARGO/EXT STORES IN FUSE CGCF .0 IN 
FUSELAGE FUEL CGZWF .0 IN 
WING FUEL CGFWF . 0 IN 
AIR INDUCTION SYSTEM CGN .0 IN 
AIR CONDITIONING CGAC .0 IN 
AUXILIARY GEAR CGAI ,0 IN 
AUXILIARY TANKS CGAUT .0 IN 
AMMO AND NONFIXED GUNS CGAMMO .0 IN 
MISCELLANEOUS USEFUL LOAD CGMIS 0 IN 
F16-FLOPS-OUT 
» NAMELIST SCONFIN 
GEOMETRIC RATIOS. OBJECTIVE FUNCTION FACTORS, AND DESIGN VARIABLES 
DESCRIPTION NAME 
DESIGN RANGE DESRNG 
WING LOADING REQUIRED WSR 
THRUST/WEIGHT REQUIRED TWR 
GLOVE/WING AREA REQUIRED PGLOV 
HORIZ TAIL VOLUME COEF HTVC 
VERT TAIL VOLUME COEF VTVC 
COST CALCULATION SWITCH I COST 
VALUE DIMENSIONS 
580 .6 N MI 
.00 
.ooooo 
.ooooo 
.000000 
.000000 
0 
FUNCTION TO BE OPTIMIZED - OBJ 
+ ACH«(L/D) + 
t SIONS) 
DESIGN VARIABLE DATA 
VARIABLE 
SCALE FACTOR NAME 
, 0000*(RAMP WEIGHT) + 1.0000*FUEL + ,0000*M 
. 0000*RANGE + ,0000*COST + .0000*(NOX EMIS 
VALUE ACTIVITY LOWER BOUND UPPER BOUND 
RAMP WEIGHT, LBF GW 
.00000 
WING ASPECT RATIO AR 
,00000 
THRUST PER ENGINE, LSF THRUST 
.00000 
REF WING AREA, SQ FT SW 
.00000 
WING TAPER RATIO TR 
.00000 
WING 1/4 CHORD SWEEP, DEG SWEEP 
,00000 
WING T/C TCA 
. 00000 
CRUISE MACH NUMBER VCMN 
.00000 
32974.0 
3.0000 
24350,0 
300.0 
.22750 
30 .00 
. 04O00 
.80000 
.0 
2.0000 
20000.000 
400.0 
.ooooo 
.00 
,00000 
.ooooo 
.0 
4.0000 
35000.000 
600.0 
.00000 
.00 
.00000 
.ooooo 
MAX CRUISE ALTITUDE, FT CH 50000.0 0. 
. ooooo 
TURBINE INLET TEMP (R) ETIT .00 0. 
.ooooo 
OVERALL PRESSURE RATIO EOPR . 000 0. 
.00000 
FAN PRESSURE RATIO EFPR .0000 0. 
.00000 
BYPASS RATIO EBPR .0000 0. 
,00000 
THROTTLE RATIO ETTR .00000 0. 
.00000 
,0 
.00 
.000 
. oooo 
.0000 
.00000 
.0 
.00 
.000 
, oooo 
.0000 
.ooooo 
It NAMELIST $AERIN 
AERODYNAMIC OPTIONS AND APPROXIMATE TAKEOFF AND LANDING DATA 
DESCRIPTION NAME 
AERODYNAMIC INPUT METHOD MY AERO 
WAVE DRAG INPUT SWITCH IWAVE 
WAVE DRAG FACTOR FWAV
LINEAR/PARABOLIC INTERP ITPAER 
AERO MATRIX FORMAT SWITCH ISO 
MAX CAMBER AT 70 PERCENT 
SEMISPAN CAM 
AIRCRAFT BASE AREA SBASE 
WING TECHNOLOGY AITEK 
MODIFY EDET DATA MODARO 
FIXED DESIGN CL FCLDES 
TURBULENT/LAMINAR FLOW XLLAM 
AERO EFFICIENCY FACTOR E 
OVERRIDE PARAMETERS FOR WETTED AREAS 
VALUE DIMENSIONS 
1 
1 
1.0000 
2 
C 
,00000 PERCENT CHORD 
.0 SQ FT 
1.0 
0 
-1.0000 
.0 
1.0000 
SWETW 
SWETH 
SWETV 
SWETF 
SWETN 
1 . OOOC 
WING WETTED AREA 
HOR. TAIL WETTED AREA 
VERT, TAIL WETTED AREA 
FUSELAGE WETTED AREA 
NACELLE WETTED AREA 
TAKEOFF AND LANDING DATA 
RATIO OF MAX. LANDING WT, 
TO MAX. TAKEOFF WT. 
MAX. LANDING VELOCITY 
MAX. TAKEOFF FIELD LENGTH 
MAX. LANDING FIELD LENGTH 
MAX. CL TAKEOFF CONFIG. 
MAX. CL LANDING CONFIG. 
APPROACH CL 
AIR DENSITY RATIO 
L/D RATIO 2ND SEG. CLIMB 
L/D RATIO MISSED APPROACH 
THRUST PER ENGINE TAKEOFF 
THRUST PER ENGINE 2ND 
SEG. CLIMB 
THRUST PER ENGINE MISSED 
APPROACH 
It NAMELIST SENGDIN 
ENGINE DECK CONTROL, SCALING AND USAGE DATA 
0000 
0000 
oooo 
oooo 
WRATIO .9565 
VAPPR 150.0000 KTS 
FLTO 12000.0 FT 
FLLDG 12000.0 FT 
CLTOM 2.0000 
CLLDM 3.0000 
CLAPP .0000 
DRAT 10 1.0000 
ELODSS .oooo 
ELODMA .0000 
THROFF .oooo 
DESCRIPTION NAME 
ENGINE DECK PRINT CONTROL NGPRT 
VALUE DIMENSIONS 
1 
I5:07:S3 
ENGINE DECK SCUflCE SWITCH I GEN EN -1 
SLCFE FACTOR FOR 
EXTRAPOLATING FUEL FLOWS EXTFAC 1 
SU5S0NIC FVKt, FLOW FACTOR PPPsUa 1 OOOO 
SUPERSOWIC FUEL y./Jrl FACT I . LL ' 1 00C0 
FLKJHT IDLE SWITCH I DLL u 
IGNORE NEGATl\r= THRUSTS NOM77G 0 
SFC EXTRAPOLATION SWITCH IXTRAP I 
PART POWER DATA SWITCH IFILL 3 
MAX. CRUISE POWER SETTING MAXCR 2 
BOOST ENGINE SWITCH BOO: r 0000 
FUEL FLOW SCALING 
CONSTANT TERM DFFA.C oooo 
FUEL FLOW SCALING 
LINEAR TERM FFFAC oooo 
NITROGEN OXIDES SWITCH NOX 0 
INSTALLATION DRAG SWITCH 7NSDRU 0 
SW; [NE DECK FILE NAHFJ EIFILE GE12 3. 
F16-
# ALL POINT ENGINE DECK SUMMARY 
HACH = 1.600, ALTITUDE * 50000., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
j '539.'; 3 544. :014.0 2012.0 809.0 (11.0 
2245B.C 4926.2 4166.7 3490.8 2599.2 234B.4 
2.131 1.390 1482 1.735 3,213 3.300 
757 ' 1 .600, ALTITUDE 
t}431.n 1472.0 3802.0 
2 8597.4 f. 166.9 ^5 92.7 
2.121 1.379 1.471 
= 45000 , Tiir.USTS/1 LJJ-.I '-LOWS/SFCS/NOX RATIOS FOLLOW 
2536.0 1013.0 771.D 
4364.5 3241.6 2J31,9 
].721 3.200 3.788 
HACH = 1.600, ALTITUDE = 40000., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
17212.0 5658.0 4804.Q 3192.0 1266.0 9*7.0 
36386.2 7/57.1 7018.1 5455.1 4C49.9 36*2.0 
2.114 1.371 1.461 1.7*9 3.199 3.787 
MACH = 1.600, ALCi'l fJIK 35000., TKHUSTS/FUEL FLOWS / SFtS/NOX RATIOS FOLLOW 
213,45.0 6977.0 5BB7.0 3892.0 1537.0 1215.0 
45998.6 9573.9 86957.1 6791.5 5116.8 4615.3 
2.135 1.373 1.477 1.7' i 3.204 3.799 
MACH - 1.600, ALTITUDE ~ 30000.. THRUSTS'FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
24BJ4.0 710/.0 £157.0 4075.0 LuS7.0 1600.0 
5552*. J 10326,5 9709.6 L'121.0 6647.8 6031.6 
2.275 1 433 1.577 1.988 3.193 3.751 
MACH - 1.60G, ALTITUDE = 25000., THRUSTS/PL"!L FLOWS/SFCS/NOX RATIOS FOLLOW 
27649.0 6773.0 559.1.0 3823.0 2657.0 2052,0 
6503O.4 11040 O 10259.5 9224.9 8411.7 7639.2 
2.1.S2 1 . 63 0 1 75 2,4 13 3.154 1.729 
MACH K l.EOO, ALTITUDE 
2B7O0.0 9169.0 35 33,0 
726*8.4 112/3.6 101BS.4 
2. Hi 2.181 2.666 
= 20000., THRUSTS/FLTT7T. FLOWS/SFCS/NOX RATIOS FOLI ;Vi 
2883.0 2882,0 2793.17 
9862.7 9859.3 9750.4 
3.421 3.421 3.491 
MACH = J . EiiO, ALTITUDE 
9S.il.G 3555,0 29H7.0 
20473.4 4745.9 4229.8 
2.072 1.335 1,111 
MACH = 1.5Q0, ALTITUDE 
12*36.0 4490.0 3143.0 
26046,9 5944.8 5296.2 
2.301 1.3-21 1.400 
= 50000., T31RUSTS/FUKL 
2027.0 735.0 611.0 
3206.7 27,22,3 2073.9 
1.582 2.031 3.296 
= ISDOO., TKBUSTS/FUEL 
2555,0 933.0 TS6.0 
4007.9 2768.1 2510.2 
1.5*6 2.B1E 3.27/ 
FLOWS/SFCS/NOX KATTCS FOLLOW 
FLOWS/Si-CS/NOX RATIOS FOLLOW 
OUT 
MACW = 1-500, ALTITUDE = 4G000-, THRUSTS/FUEL FLOW5/SFCS/NOX RATIOS FOLLOW 
16127.0 SB74.D 1750.0 1222.0 1230.0 959.0 
J3I03.7 7467, D 65S3.Q 5017.4 3455.1 iuO.: 
2.0 = 3 1.316 I..-:-': 1.556 2,803 3.26: 
MACH - 1.SO0, ALTITUDE = 35000., TFiRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
20162.0 5S67.0 5852.0 394B.0 1515.0 1200.0 
41739.3 9224.3 8192,S 6233.9 1350.7 1937.2 
2.O70 1.J24 I.4CO 1,579 2.816 3.231 
MACH = 1.5O0, ALTITUDE = 30000., THRUSTS/FUEL FLOWS / SFCS / NOX K.AT I LH> FOLLOW 
21452.0 7423.0 6475.0 4235.0 199D.0 1513.0 
50867.4 10243.2 95*1.1 7451.8 S615.7 50BZ.6 
2.169 1,37 5 1.4 74 1.73 5 2.832 3.2 94 
MACH = 1.500, ALTITUDE = 25000., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOI,LOW 
26320.0 7613.0 660S.O 4003 . 0 2550.0 ,.992.0 
60881.4 11122.6 10402.9 884C 1 7239.4 6533.8 
2,270 1.461 1.575 1.918 2.S39 3.2.-I0 
MACH = 1.500, ALlIT/'ilJE - 20000-, THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
29605.0 7275.0 6122.0 4459,0 3264.0 2551.0 
70637.5 11931,0 11074.7 9988.2 9077.2 829*.7 
2.386 7.640 1.809 2.240 2.7.71 3.249 
MACH = 1.500, ALTITUDE = 15000.. THRUSTS/r'Ui-;L FLOWS/SFCS/NOX RATIOS FOLLOW 
30874,0 5854.0 4667.0 3523.0 333J.0 .0 
78B21.3 12240,7 11396.6 10635.9 10434,5 .0 
2.55J 2.091 2.442 3.019 3.112 .0-00 
MACH = 1.4DD, ALTITUDE =. 500OO., THRUSTS/F'JEL FLOWS/SFCS/NOX RATIOS FOLLOW 
9256.0 3456.0 2978.0 2018.0 833.0 6*9.0 
I6B73.0 4472.5 3945.8 2905.9 7917.6 17-10.1 
2.039 1.233 1.325 1,110 2.302 2.601 
MACH = 1.400, ALTITUDE = 4r-,n00., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
11828.0 4336.0 3715.0 2550.D 1046.0 342,0 
23999,0 5579.0 491 3.4 36(3.8 2337.0 2168.2 
2.029 1.272 1.312 1.425 2,282 2.575 
HACH =1 , ALTITUDE = 4000U., THRUSTS/FUEL FLOWS/SFVS/NOX RATIOS FOLLOW 
15082.0 5SOS.0 4701.0 321B.0 1313.0 1057,0 
30495.8 5345.6 6116.0 -1550.3 2979,2 2703.8 
2.022 1.261 1.301 1.414 2.269 2.55B 
MACH = 1.400, ALTITUDE = J50O0., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
18952.0 6889.0 5S40.0 4016.0 1648.0 1326.0 
38283.0 B693.9 7677.0 5698.7 3742.6 3394.6 
2.020 1.2,62 1.306 1 413 2.271 2.560 
MACH = 1.400, ALTITUDE = 3QCP"., THRUSTS FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
22097.0 7739,0 *S58.0 4517.0 2083,0 1667.0 
46201.6 10111,3 9004.1 SS52.3 4805.5 4340.9 
2.091 1.302 1.373 1.517 2.j07 2.604 
MACH = 1.40O, ALTITUDE 25000., THRUSTS/I 3 FLOWS/SFCS/NOX RATIOS PLT.I.OW 
25522,0 8170.0 7291.0 4J71.0 2646.0 2121.0 
5:514.6 11012.2 103tC 5 B127.6 fii«2.5 5.39.1 
2.137 1.34B 1.421 1.635 2.329 2,f21 
MACH - 1.400, ALTITUDE = 20000., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
23941.0 3406.0 741B.0 5474.0 3337.0 2688.0 
66188.1 120D3.8 11208.6 9579.5 7341.9 7077.5 
2.777 1.428 1.511 1.750 2.150 2.633 
«AC» 1 * .. "x i'E = 1 j., TIT s, Ui-77 RWJWFL,.- */NOX .CP 77r7,1,0W 
31372.• 8248, (J 7125.0 5519.0 ,1^34.0 3422.0 
7S460.9 12941 . J 32019.9 10844-8 9755.1 8904.D 
2 199 1.589 1.687 1.965 J.304 2.6D2 
I4ACJI = 1.4,1Q, ALTITUDE = : i ... rnflSTS/FOEL FLOWS/SFCS/NOX RATIOS FOLLOW 
315)12,0 709B.0 5908.0 4716.0 4350.0 .0 
854*1.1 iJi44.2 12449.: I±5i0.t .
2.550 l.ee-0 20B6 2.445 2.556 .000 MACH =
 1 300, ALTITULIfc - 50000.. TS FUEL FLOWS/SPCS/NOX RATIOS FOLLOW 
B450.0 3249.0 2814.0 1663-0 603 0 .0 
1714 6.6 4045 0 3S8S.0 2594 f 155'j.j .0 2.034 1.245 1.274 1.378 2,561 .000 
KACri = 1.300, ALTITUDE - 45000., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
10510.0 4 90.0 3545 0 23S0.0 7511.0 .0 21570.1
 5038.9 1170.2 3241.6 1933.7 .0 
2.024 1.232 1.261 1.362 2 . sul .000 
MACH = 1.300. ALTITUDE = 40003., THRUSTS /FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
13842.0 5140.0 4415.0 3007.0 9SD.0 .0 
27947.C 6275.9 5564.3 4056.4 2403.2 .0 
2.019 1.221 1.249 1.349 2.535 .0 00 
MACH - 1.300. ALTITUDE = 35000., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLtiOW ncOO.lj 6J21.0
 5537. 0 3748.0 1157,0 .it 
35402.5 7833.6 692E..O 5071.0 J003.9 .0 
2.023 1.220 1.251 1.353 2.574 .000 
SACS = 1.10D, ALTTTULE - 30000., THRUSTS/FUEL FLOWS/SFCS/NOX f/.' . FOLLOW 
20769.0 7670.0 5473.0 4455.0 1317.0 L0 
42306.5 9545.2 H3B9.0 5286.0 3720.5 .0 
2.0J7 1.251 1.296 1.411 2.825 .000 
MACH - 1.300, ALTITUDE = 2 50-70., THRUSTS/FUE: i/LOWS/SFCS/NOX RATIOS FOLLOW 
23986-0 6572.0 7295.0 49B6.0 1363.0 .0 
50600.6 10989.3 9B34.8 7494. G .1504.7 .0 
2.118 1.2E2 1-350 1,503 3.305 .000 
HACK = 1.300, AL'll.UDE = 20000., TliMJ: ."S/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
27450,0 8904.0 7971.0 5473,0 1139.t .0 
60856.7 11366.8 11160.8 8833.4 5485.5 .0 
2.217 1.335 1.40f L.614 3.912 .000 MACH - 1.300,
 ALT J i'L/I-E 15000., THRUSTS/FUEL FLOWS.SFCS/NOX RATIOS FOLLOW J0669.0 9181.0 8139.0 6070.0 IB.5B.0 .0 V!t,.]t.9 13000.3 (1141.4 10311.4 0G34,6 .0 
2.321 1.416 1.492 L.7C6 3.735 .000 HACK »
 1.30O, ALTITUDE 10030., THRU5T3/ FUEL FLOWS/SFCS/NOX RATIOS PUJjLOW 
33856.0 8139.0 7344.0 6146.0 2420.0 16)9.0 
82*73.. 2 14110.6 13107.6 11714.3 8651.5 7458.6 
2. A 1.5411 1.650 1.506 3.575 4.854 
MACH - 1.3 0D, ALTITUDE - 5000., THRUSTS/FUEL FLOWS/SFCS/NOX i.Ai'iOS FOLLOW 
34385,0 8061.0 6B72.0 S237.0 3055.0 2275.9 
89323.8 14522,7 llSfil.5 12443.1 10!;30.3 9814.4 
3,597 l.aii 1.388 2.376 3.496 4.314 
MACH = 1 300, ALTITUDE - 500'iO., THSUSTS7 KJE-L FLOWS/SFCS/NOX RATI0:7 7482.0 2947.3 2l'.a2.0 1713.0 696.0 329.0 15H3,
 (j 1545.2 3168.1 2219.5 1313,3 1170.J 2.024 1.203 1.227 1.321 2.321 3.557 
MACH = 1.200, ALTITUOE 
96DR.0 3727,0 3250,0 
19312.1 4442.6 3942.2 
5,010 1.192 1.211 
s 45000., THKUSTS/FUEL FLOWS/SfCS/NOX RATIOS FOLLOW 
2172.-5 75D.D .0 
2B.34.5 1716.8 .0 
1.305 2.2B9 ,000 
OUT 
MACH - 1.20P, ALTITUDE = 40000 . , TKBUSTS/FUEL FLOWS/5FCSJUQY. RATIOS FOLLOW 12311.0 4(509.0
 4Q8B.0 2747.0 942.0 .0 
24634.3 5513.0 4913.8 3546,4 2135.3 .0 
2.001 1.130 1.202 1.291 2.267 .000 
MACH = 1.20C, ALTITUDE = 35000., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
15597.0 5S98.0 5150.0 3474.0 1175.0 .0 
31441.1 6941.9 6169.7 4471.0 2o71.9 .0 
2.003 1.177 I.IBS 1.287 2.274 .000 MJJTfl - 1.200, ALTITUDE
 ~ JOOOD., THRUSTS/E'UE^ FLOWS/SFCS/NOX FTiTTOS FOLLOW 
1S358.Q 724^.0 6239.0 4245,0 1375.0 .0 
39450.3 8694-0 7*47.7 5528.9 33289 .0 
2.0<j0 3.2UD 1.22^ 1.326 2.421 .000 
MACIi = J .200, ALTITUDE = 250CO., THRUUT5'FUEL FLOWS '"^/MOIt RATIOS FOLLOW 
22620.0 6600.0 7224.1- 4993.0 1544,0 .0 
4643R.9 10517.3 91EB.9 6905.3 4079.2 .0 
2.053 L.JJ3 1,272 1.333 2.612 .000 
MACH = 1,200, ALTITUDE: = 20000., TKRHSTS/FUEU FLOWS/SFC.5 /NOX RATIOS FOLLOW 
25932.0 J45Q.O 8155.0 5566.0 1623.0 .0 
55572.3 11B50.3 10707.1 HUH.3 4916.3 .0 
2.-43 1.254 1.113 1.46.7 3.029 ,000 
MACH = 1.200. AJ.'I . DE - 15000., THRUSTS/FUEL FLOWS/SFCS/NOX RATI * 
29451.0 " 41 0 R»54.0 6140.0 16343.0 -O 
66081.8 12BB8.4 12034.6 9565.1 St<l>7.3 .0 
2.244 1.309 1.366 1.55B 3.532 .000 
MACH = 1.200, AJ.T1TJDE - 10OO0., THRUSTS/FUEL FLOWS/Gl-Ci:/NOX RATIOS FOLLOW 
32373.0 10220.0 9II2.0 6788.0 1595.0 .0 
77317.3 14144.5 11221.5 11159.5 6970.1 .0 
2.132 :.334 1.4-51 1 .044 4,370 .000 
MACH = 1.200, ALTITUDE = 5000., THRUSTS/FUE I FLOWS/SFCS/NOX RAT-OS FOLLOW 
34656.0 13332.0 iOFi.O 0353.0 .0 ,0 
85808.3 15436.0 1434B 3 12619.7 .0 .0 
3.476 1.494 1,563 1.B15 .000 .000 
MACH - 1 . 10, ALTITUDE = 0., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
33311.0 9386.0 6138.0 6167.0 .0 .0 
89173.5 100E7.6 15044.9 13524.2 .0 .0 
2.677 1.714 1.871 2.193 .000 .000 
MACH - 1.100, ALTITUDE - 5,0000., THRUSTS/FUEL FLOWS/.'FOS/NOX RATIOS FOLLOW 658D.O
 2676.0 2348.0 1564.0 594,0 570.0 
13296.2 30B5.4 2754.2 1971.2 12Z4.8 1197.6 
2.021 1.J53 1-173 1.161 2.062 2.101 
MACH i 1.100, ALTITUDE 
B475.0 3397.0 2*55.0 
169*7.0 3876.0 3421.9 
2.0O2 1.141 1.158 
- 45000., THRUSTS/FUEL FLUUS/SYi/S/NOX RATIOS FOLLOW 
19*0 0 747.0 .0 
2461.1 1514.9 .0 
1.243 2.028 .000 
MACH -- 1.3 00. ALT.: TIDE = 40000., THRUST >: /11 ;EL FLOWS/SFCS/NOX RATIOS FOLLOW 
10B77.0 4279.0 3723.0 2507.0 943.0 .0 
21645.2 4631.0 4256.6 3076.1 1885.1 .0 
1.930 1,129 1.146 1.227 1.999 .000 
MACil = 1.100, ALT! TV33 E = ' '-00., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
139C0.O 53S1.0 4694.0 3169.0 1179.0 .0 
27633 2 6055.9 5360.5 3872.5 2355.6 .D 
1-9*8 1.125 1.14Z 1.222 1.99B .OOO 
MACH = 1.100, ALTITUDE •= 30000., THRUSTS/FUEL PLOWS / SFCS/NOX RATIOS FOLLOW 
• 1 
J18 
4716.0 
771D.J 
i. 146 
591B.O GJ.76 ' 
i 
4005.0 
4S73 .5 
I .241 
1430.0 
1940.1 2 .
 070 .• 00 
F16-FL 
MACK = 1.100, ALTITUDE = 25000., THRUSTS/FUEL-
21121.0 8161.0 7036.0 4819.0 1661.0 .0 
4 5140.3 9 = 32.0 8393.9 61(12.8 3647.6 .0 
2.052 1.168 1.193 1.283 2.196 .000 
FLOWS/SFCS/NOX RATIOS FCL1.!VJ 
MACH - 1.10D, ALTITUDE = 20OQ0 . , TRUSTS/PL! EL Fl.rlWS/SFCS/NOX RAT J 
24406.0 9642.0 8098.0 5616.0 1871,D .0 
50=20.4 : I 196.3 9944.3 74*7.4 4139.5 .0 
2.070 1.1S2 1.228 1.335 2.369 .ODO 
OS FOLLOW 
MAC SI - 1.100, ALTITUDE - 15000., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
27760.0 10483.0 9145.& 6216.0 1997.0 .0 
60155.9 12757.g 11541.0 8803.4 5308.0 .0 
l::7 L 217 1 .202 1 . 409 2 .658 , 000 
HACH - 1.10O, ALT3T:.I(;F; 10000., THRUSTS/F'JEl 
11256.0 109B* 0 9916.0 fi<U6.0 2070.0 .0 
71013.6 13919.3 13085.7 10272.2 6296.9 .0 
2.272 1.267 1.317 1.7 81 3.042 .000 
LOWS /SFCS/NOX MOS FOLLOW 
MAC11 = 1.100, ALTLTUUA = 5000., TKRWSTS/FD •" 
74406.0 11*98.0 10331.0 -7635.0 2098.0 ,0 
62092,7 15126.3 14349.8 11915.2 7437.4 .0 
2.3B6 1.333 1.JB9 1.5' . 3.545 .000 
FLOWS/SFCS/NOX RATIOS FOLLOW 
MACH - I. 130, ALTITUDE = 0., THRUSTS/FUEL FLOWS/SFCS/NOX 
3347*.0 11550.0 10479.U 7917.0 1991.0 .0 
55271.0 16574.2 15S5S.1 7145B.9 8529.0 .0 
2.bl7 1.435 1.495 1.700 4.334 .000 
70S FOLLOW 
MACH = -9D(}, ALTI7\IDE = 50000., THRUSTS y FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
4922.0 2193.0 2225.0 1557.D 1175,0 1152,0 
9253.4 1 S75.8 211ft. Q 154..-.0 1253.6 1246.5 
1.880 .953 .953 .991 l.l 16 1,082 
MACH = .900, ALTITUDE = 45000., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
6763.0 3171.0 2810.0 1976.0 1051.0 940.O 
17777.2 29S0." 2633.0 1918.7 I20B.7 1142.1 
1.978 .940 .937 ,971 1.150 1.215 
MACH * .900, ALT 1 TUi7.-: = 40Q00., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
8720.0 4021 351C.O 2507.0 1333.0 634.0 
17065.0 3735.5 3276.5 2394.2 1499.b 1049.3 
>..957 .92 7 .92 7 .955 11135 1.655 
MACH - .=.-00. ALT-ITUEE = 3 7000., THRUSTS/FUEL FLOWS/SFCS/NOX W 
11145-0 5072.0 4473.0 3176 0 1681. Fj 273.0 
21760.6 468.6.5 4110.7 3007.7 1872 6 9aO,t 
1.&49 .921 .919 .44/ 1.114 3.592 
OS FOLLOW 
MACH = .900, ALTITUDE = 3 0000 . TifRUSTS / FLLHR. 
14053.0 63B3.0 5629.0 3935.0 2074.0 .0 
27624.0 5981.2 526B.7 3A29.6 2347.3 .0 
1,965 .940 .936 .961 1.132 .000 
FLOWS •-! CS/NOX KATTOS FOLLOW 
HACH - .900, ALTITUDE J 250O0., THRUSTS/FUEL FLOtlS/SFCS/NOX RATIOS 7.77LLOW 
•• V.O 7:,7 1.0 7041.0 4S74.0 2539.0 .0 
J46B9.Q 7583.3 RJV17.1 4854.6 2919.8 .0 
1.9A7 .957 .954 .976 1,150 .000 
NftCH a .400. AiTTTUDE = 20000., THRUSTS/FUEL FLCWS/SFCS ,'HOX RATIOS FOLLOW 
21458,0 9761.0 BE4S.5 414J.D 3070.0 
43259.3 9497.5 H31V9.5 611S.3 3593.0 .0 
•OUT 
2 .016 .973 . 97,: .995 1. 172 .000 
KftCH = 
25187. 
.900, ALTITUDE = 15000., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS 
11612.0 IO093.0 7266.0 3638,0 .0 
51406,7 11391,4 
2.041 .981 
9 37 5.B 
,98S 
7411...! 
1.02D 
4365.6 
1.200 
.0 
, ODD 
HACH 1 ,DDD. ALTITUDE = IOOOO. , THRUSTS/Fl.'KL FLOWS/SFCS/NOX RAm. • FOLLOW 
23583.0 13469.0 1161B.0 8347.0 1229.0 .0 
•3.5 13374.7 11613.0 B7S9.6 5231.3 0 
2.LJ0 .993 1.000 1.046 1.237 .000 
HACH = .900, AL 'UDE = 5DOO., THRUSTS/FUEL FLOWS/SFCS/NOK RATIOS FOLLOW 
31789.Li 14776.0 13093.0 9416.0 4796.0 .0 
69957.6 14968.1 13361.0 10209.S 6162.9 .0 
2.201 1.013 1,022 1.032 1.2*5 .000 
KACH = .-jj, ALTITUDE s 0., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
11964,0 16003.0 14319.0 10443.0 540S.O .0 
7B970.9 16579.1 15004.1 11738.1 7235.9 .0 
2.325 1.036 1.04* 1,105 3.338 .000 
MACH = .BOD, ALTITUDE • 50000., THRUSTS/FUEI, 
3970.0 228B.0 2058.3 1457.0 13±0.0 1291.0 
6756.9 3091.2 1874.8 13^7.1 1273.3 126*.5 
1.702 .914 .J11 .952 .972 .931 
LOWS/SFCS/NOX RATIOS FOLLOW 
MACH = .300, ALTITUDE • 4 5 00 
5979.0 2916.0 2619.G 1818,0 
11916.1 2624.4 2315.2 1722,3 
1.993 .700 .c97 .932 
)., THK-'.-TS/FUEL FL07.7-/5FCS/NOX RATIOS FOLLOW 
1144.0 1099.0 
117,..6 1164.9 
1.025 1.060 
MACH = .300, ALTITUDE • 40000., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
7737,0 3710 0 3303.0 2346.0 1310.0 823.0 
15203.2 3294.5 2919 9 2146.6 1354.5 1065.B 
1.965 ,BB3 .881 .915 1.034 1.295 
MACH = .ROD, ALTITUDE » 35000., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
•1929.0 4711.0 4167.0 2973.0 1654.0 519.0 
19391.2 4164 5 3658 6 2573.5 165S.7 996.5 
1,953 .884 .878 .906 1.021 1.920 
MACH = .8011, ALTITUDE = 30050., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
1250B.0 5911.0 5228.0 3723.0 2041.0 . u 
24590.7 5314.0 4668.6 34 7.7 2118.6 .0 
1-966 .499 .893 .918 1.078 .000 
KACH = .B00, ALTITUDE = U5000., THRUSTS! J/Uj:i. 
15603.0 7357.0 6531.0 46.35 0 2499.0 .0 
30929.1 6731,7 5943.2 4315.2 2631.4 .0 
1.982 .915 ,910 .931 1.053 .000 
•"LOWS/SFCS/NOX i^.TICS FOT7 7W 
MACH = .HOO, ALTITUDE = 20000., THRUSTS/FUH 
192B1.Q 9077.0 0D93.O 5745,0 3038.0 .0 
33653.4 8.450.7 7434.1 5434.8 1217.6 .0 
2.005 .931 ,926 .946 I.069 .000 FLOWS/SFCS/NOX Y.iW\ I OS FOLLOW 
MACH = ,800, ALTITUDE = 15D0D., THR'/S 7S/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
23342.0 11029.0 9716,0 6970.D 3635. 0 .0 
47107.!; 10433.4 910D.7 67S6.1 335.8.5 .0 
2.031 .946 .942 .965 1,089 .000 
MACH = .ot-Q, ALTITUDE - 3( 000., THRUSTS.'FJEL FLOWS/SFCS/NOX RATIOS FOLLOW 
27045.0 33135.0 11369,0 8204.0 128!).0 .9 
55*58.6 12517.7 10868.8 11105.6 4777.9 .9 
2.059 .953 .956 .988 1.114 .000 
Nov 18 96 
MACH = .700, ALTITUDE = 50O00., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
3378.0 2141.0 1932.0 1434.0 1415.0 .0 
5344.0 1873.4 1680.8 1289.2 1284.8 .0 
1.582 .875 .870 .899 .908 .000 
MACH = .700, ALTITUDE = 45000., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
5234.0 2728.0 2463.0 1779.0 1292.0 1244.0 
10106.9 2348.8 2105.9 1563.7 1192,5 1184.3 
1.931 .861 .855 .879 .923 ,952 
MACH = .700, ALTITUDE • 40000., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
6962.0 3472.0 3136.0 2257.0 1280.0 996.0 
13743.0 2947.7 2643.6 1947.8 1233.9 1082.7 
1.974 .349 .843 .863 .964 1.087 
MACH = .700, ALTITUDE = 35000., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
8960.0 4414.0 3958.0 2859.0 1617.0 708.0 
17525.8 3725.4 3312,8 2441.6 1537.8 1006.8 
1.956 .844 .837 ,854 .951 1.422 
MACH = .700, ALTITUDE = 30000., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
11286.0 5573.0 4950.0 3578.0 1996.0 366.0 
22199.6 4781.6 4207.5 3095.0 1924.1 960.0 
1.967 .858 .850 .865 .964 2.623 
MACH = .700, ALTITUDE = 25000., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
14114.0 6944.0 6163.0 4444.0 2447.0 .0 
27917.5 6069.1 5324.8 3888.5 2390.7 .0 
1.978 .874 .864 .875 .977 .000 
MACH = .700, ALTITUDE = 20000., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
17521.0 8572.0 7650.0 5490.0 2975.0 .0 
34954.4 7620,5 6747.3 4875.1 2945.2 .0 
1.995 .889 .882 .888 .990 .000 
MACH = .700, ALTITUDE = 15000., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
21445.0 10488.0 9397.0 6760.0 3592.0 .0 
43276.0 9481.2 8419.7 6111.0 3606.4 .0 
2.018 .904 .896 .904 1.004 .000 
MACH = .700, ALTITUDE = 10000., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
25559.0 12589.0 11085.0 8071.0 4259.0 .0 
52217.0 11518.9 10087.4 7433.4 4361.2 .0 
2.043 .915 .910 .921 1.024 .000 
MACH = .600, ALTITUDE = 500OO., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
2918.0 2005.0 1815.0 1526.0 1494.0 .0 
4362.4 1698.2 1528.2 1298.6 1299.8 .0 
1.495 .847 .842 .851 .870 .000 
MACH - .600, ALTITUDE = 45000., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
4437.0 2555.0 2312.0 1722.0 1412.0 1354.0 
7911.2 2125.8 1907.4 1436.1 1208.7 1201.0 
1.783 .832 .825 .834 .856 .887 
MACH = .600, ALTITUDE = 400OO., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
6277.0 3253,0 2946.0 2136.0 1265.0 1152.0 
OUT 
12510.1 
1.993 
2664.2 
.819 
2392.2 
. 812 
1786.0 
.817 
1138.5 
. 900 
1100.2 
.955 
MACH = .600, ALTITUDE = 35000., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
B099.0 4139.0 3748.0 2768.0 1599.0 896.0 
15963.1 3365.0 3017.1 2236.5 1416.7 1017.0 
1.971 .813 .805 .808 .886 1.135 
MACH = .600, ALTITUDE = 30000., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
10217.0 5216.0 4689.0 3462.0 1976.0 635.0 
20209.2 4308.4 3830.9 2828.5 176S.5 968.4 
1.978 .826 .817 .817 .895 1.525 
MACH = .600, ALTITUDE = 25000., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
12781.0 6543.0 5823.0 4295.0 2423.0 302.0 
25395.8 5496.1 4833.1 3547.7 2195.2 933.5 
1.987 .840 ,830 .826 .906 3.091 
MACH = .600, ALTITUDE = 20000., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
15940.0 8094.0 7210.0 5297.0 2950.0 .0 
31832.2 6928.5 6099.7 4433.6 2705.2 .0 
1.997 .856 .846 .837 .917 .000 
MACH = .600, ALTITUDE = 15000., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
19616.0 9910.0 8867.0 6507.0 3567.0 .0 
39526.2 8631.6 7634.5 5537.5 3310.2 .0 
2.015 .871 .861 .851 .928 .000 
MACH = .600, ALTITUDE = 10000., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
23780.0 12037.0 10779.0 7940.0 4279.0 .0 
48439.9 10652.7 9431.6 6376.0 4026.5 .0 
2 .037 .885 .875 .866 .941 . 000 
MACH = .500, ALTITUDE = 45000., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
2428.0 2081.0 1461.0 1460.0 1410.0 .0 
1954.5 1666.9 1202.4 1201.6 1198.5 .0 
.805 .801 .823 .823 .850 .000 
MACH = .500, ALTITUDE = 40000., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
5797.0 3088.0 2652.0 1852.0 1269.0 1202.0 
11541.8 2442.6 2039.8 1489.0 1101.5 1093.8 
1.991 .791 .788 .804 .868 .910 
MACH = ,500, ALTITUDE = 35000., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
7468.0 3923.0 3369.0 2350.0 1157.0 945.0 
14712.0 3079.6 2627.8 1861.2 1086.4 1007.4 
1.970 .785 .780 .792 .939 1.066 
MACH = .500, ALTITUDE = 30000., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
9451.0 4955.0 4239.0 2945.0 1434.0 691.0 
18656.3 3944.2 3348.8 2356.0 1358.0 958.4 
1.974 .796 .790 .800 .947 1.387 
MACH = 
11791.0 
23405.1 
1 . 985 
.500, ALTITUDE 
6207.0 5263.0 
5021.5 4215.7 
.809 .801 
= 25000., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
3666.0 1766.0 365.0 
2962.1 1684.8 920.2 
.808 .954 2.521 
MACH = .500, ALTITUDE = 20000., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
14656.0 7720.0 6511.0 4537.0 2160.0 .0 
29253.4 6361.3 5300.0 3697.7 2082.2 .0 
1.996 .824 .814 .815 ,964 .000 
MACH = .500, ALTITUDE = 15000., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
18010.0 9470.0 8033.0 5585.0 2625.0 .0 
36272.1 7935.9 6667.4 4607.6 2556.8 .0 
2.014 ,838 .830 .825 .974 .000 
15:07:53 F16 
MACH = .800, ALTITUDE = 5000., THRUSTS/FUSL FLOWS/SFCS/NOX RATIOS FOLLOW 
30409.0 14960.0 12952.0 9386.0 4938.0 .0 
64679.9 14481.3 12550.5 9508.0 5673.8 .0 
2.127 .968 .969 1.013 1,149 .000 
MACH = .800, ALTITUDE = 0., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
33581.0 16293.0 14503.0 10594.0 5579.0 .0 
75322.2 16064.9 14372.5 10986.0 6644.6 .0 
2.243 .986 .991 1.037 1.191 .000 
MACH = .400, ALTITUDE = 40000., THRUSTS/FUEL FLOWS/SPCS/NOX RATIOS FOLLOW 5271.0 2929.0 2510.0 1762.0 1370.0 1307.0 10083.4 2226.0 1882.5 1363.8 1112.4 1107,0 
1.913 .760 .750 .774 .812 .847 MACH = .400, ALTITUDE - 35000., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
6930.0 3721.0 3185.0 2235.0 1154.0 1061.0 13499.6 2798.2 2363.3 1705.3 1028.2 1016.4 1.948 .752 .742 .763 .891 .958 
MACH = .400, ALTITUDE = 30000., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 8782.0 4694.0 4011.0 2795.0 1395.0 807,0 17133.7 3572.1 3016.3 2152.2 1259.7 966.8 
1.951 .761 .752 .770 .903 1.198 MACH = .400, ALTITUDE = 25000., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
10972.0 5869.0 4997.0 3471.0 1715.0 499.0 21516.1 4530.9 3807.7 2697.0 1560.7 927.1 1.961 ,772 .762 .777 .910 1.858 
MACH = .400, ALTITUDE = 20000., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 13590.0 7288.0 6161.0 4282.0 2096.0 ,0 2678S.9 5728.4 4762.5 3357.1 1924.1 .0 
1.971 .786 .773 .784 .918 .000 MACH = .400, ALTITUDE = 15000., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
16703.0 8978.0 7572.0 5256.0 2545.0 .0 33172.2 7191.4 5959.2 4162,8 2361.8 .0 1.986 .801 .787 .792 .928 .000 
MACH = .400, ALTITUDE = 10000., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 20327.0 10898,0 9259.0 6429.0 .0 .0 40776.0 8871.0 7425.7 5156.1 .0 .0 
2.006 .814 .802 .802 .000 .000 MACH = .400, ALTITUDE = 5000., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
24504.0 13140.0 11224.0 7825.0 3680.0 .0 49669.6 10866.8 9147.6 6377.4 3485.0 .0 2.027 .827 .815 .815 .947 .000 
MACH = .400, ALTITUDE = 0., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 28775.0 15647.0 13289.0 9303.0 4361.0 .0 58960.0 13065.2 10990.0 7721.5 4190.9 .0 
2.049 .835 .837 .830 .961 .000 MACH = .300, ALTITUDE = 35000., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
6452.0 3574.0 3039.0 2147,0 1251.0 1173.0 12452.4 2562.6 2148.6 1571.6 1029.6 1022.9 1.930 .717 .707 .732 .823 .872 
MACH = .300, ALTITUDE = 30000., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 8185.0 4497.0 3824.0 2680.0 1373.0 909.0 15805.2 3264.8 2734.2 1977,3 1178.0 966.3 
1,931 .726 .715 .738 .858 1,063 MACH = .010, ALTITUDE = 50000., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
5857.0 2608.0 2310.0 1586.0 925.0 905.0 11760.9 2699.3 2402.4 1733.5 1228.4 1219.0 2.008 1.035 1,040 1.093 1.328 1,347 
MACH = ,010, ALTITUDE = 45000., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 7566.0 3314.0 2912.0 2010.0 934.0 620.0 15010.9 3386.9 2984.8 2160.8 1349.6 1114.1 
1.984 1.022 1.025 1.075 1.445 1.797 MACH = .010, ALTITUDE - 40000., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
9732 .0 19152 .6 1.968 4191.0 3674.0 2548.0 1183.0 244.0 4237.1 3721.8 2698.3 1676.3 1030.4 1.011 1.013 1,059 1.417 4.223 
MACH = .010, ALTITUDE 12447.0 5282.0 4634.0 24433.5 5319.0 4671.1 
1.963 1.007 1.008 
= 35000., THRUSTS/FUEL 3226.0 1487.0 .0 3393.8 2092.2 .0 
1.052 1.407 .000 FLOWS/SFCS/NOX RATIOS FOLLOW MACH = ,010, ALTITUDE 
15626,0 6626.0 5846.0 31017.6 6785.0 6003.8 1.985 1.024 1.027 = 30000., THRUSTS/FUEL 4059.0 1825.0 .0 4339.1 2626.2 .0 1.069 1.439 .000 FLOWS/SFCS/NOX RATIOS FOLLOW 
MACH = .010, ALTITUDE 19394.0 8227.0 7311.0 39059.5 8572.5 7640.0 
2.014 1.042 1.045 
= 25000., THRUSTS / FUEL 5090.0 2222.0 .0 5537.9 3270.8 .0 
1.088 1.472 .000 FLOWS/SFCS/NOX RATIOS FOLLOW MACH = .010, ALTITUDE = 20000., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
23161.0 9857.0 8573.0 6051.0 2613.0 .0 47294.8 10418.8 9156.0 6771.1 3990.1 .0 2.042 1.057 1.068 1.119 1.527 .000 
MACH = .010, ALTITUDE = 15000., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 26518.0 11579.0 9881.0 7029.0 3024.0 .0 54998.3 12331.6 10750,5 8125.5 4820.3 .0 
2.074 1.065 1.088 1.156 1.594 .000 MACH = .010, ALTITUDE = 10000., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
29811,0 12646.0 11161.0 7887.0 3382.0 .0 64928.4 13809.4 12433.4 9480.2 5722.3 .0 2.178 1.092 1.114 1.202 1.692 .000 
MACH = .010, ALTITUDE = 5000., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 33267.0 13448.0 12216.0 8876.0 3762.0 .0 76181.4 15115.6 14036.2 11006.2 6749,0 .0 
2.290 1.124 1.149 1.240 1.794 .000 MACH = .010, ALTITUDE = O,, THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
33659.0 14304.0 13013.0 9850.0 4162.0 .0 81757.7 16692.8 15537.5 12706.5 7932,8 .0 2.429 1.167 1.194 1.290 1.906 .000 
MACH = .000, ALTITUDE = 20000., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
11697.0 6972.0 5945.0 4137,0 2226.0 571.0 21768.1 4545.7 3804.8 2702.9 1562.7 849.1 1.861 .652 .640 .644 .711 1.487 
MACH = .000, ALTITUDE = 15000., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 14365.0 8576.0 7310.0 5137.0 2704.0 618.0 26862.5 5703.0 4751.5 3339.1 1936.1 843.6 
1.870 .665 .650 .650 .716 1.365 MACH = .000, ALTITUDE = 10000., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 17511.0 10472.0 8910.0 6253.0 3262.0 638.0 
32973.2 7110.5 5898.4 4102.0 2355.2 854.3 1.883 .679 .662 .656 .722 1.339 MACH = .000, ALTITUDE = 5000., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 
21164.0 12640.0 10811.0 7587,0 3913.0 655.0 40190.4 8721.6 7286.6 5045.4 2848.7 875.7 1.899 .690 .674 .665 .728 1.337 
MACH = .000, ALTITUDE = 0., THRUSTS/FUEL FLOWS/SFCS/NOX RATIOS FOLLOW 25381.0 15150.0 13031.0 9166.0 4672.0 743.0 48630,0 10605.0 8926.2 6177.9 3433.9 974.8 
Nov 18 96 
15:07:53 
1.916 .700 . 685 .735 1.312 
tt NAMELIST SMISSIN 
PERFORMANCE CONTROLS AND FACTORS AND MISSION SEGMENT DEFINITION 
DESCRIPTION NAME VALUE DIMENSIONS 
ENDURANCE MISSION SWITCH INDR 0 
OVERALL FUEL FLOW FACTOR FACT 1 . 0000 
CDO FACTOR FCDO 1 .oooo 
CDI FACTOR FCDI 1 .0000 
SUBSONIC CD FACTOR FCDSUB 1 .0000 
SUPERSONIC CD FACTOR FCDSUP 1 .0000 
ENGINE SCALING SWITCH ISKAL 1 
OWE FACTOR OWFACT r-i .0000 
PRINT FLAG I FLAG 2 
DETAILED MISSION PRINT MSUMPT 0 
TEMPERATURE DEVIATION DTC .0 DEG C 
CALC RAMP WT OR RANGE IRW 1 
RANGE TOLERANCE RTOL .0010 N MI 
ATA TRAFFIC ALLOWANCE I ATA 0 
WEIGHT INCREMENT DWT 1. LBF 
ROUND OPERATIONS AND TAKEOFF INPUT 
TAKEOFF TIME TAKOTM ,5 MIN 
TAXI-OUT TIME TAXOTM 6.5 MIN 
APPROACH TIME APPRTM .0 MIN 
APPROACH FUEL FLOW FACTOR APPFFF 2 .00 
TAXI-IN TIME TAXITM .0 MIN 
TAKEOFF POWER SETTING ITTFF 1 
TAXI FUEL FLOWS WILL BE FROM THE ENGINE DECK 
INPUT FOR 2 CLIMB SCHEDULES 
MINIMUM CLIMB MACH NUMBER 
MAXIMUM CLIMB MACH NUMBER 
MINIMUM CLIMB ALTITUDE 
PT 
MAXIMUM CLIMB ALTITUDE 
FT 
NUMBER OF CLIMB STEPS 
CLIMB OPTIMIZATION FACTOR 
FOLLOWING CRUISE SEGMENT 
DRAG COEFFICIENT INCREMENT 
NO. OF POWER SETTINGS 
STORE DRAG DURING CLIMB 
MAX CLIMB POWER SETTING 
FAA CLIMB ENFORCED 
FAA DESCENT ENFORCED 
MINIMUM CLIMB RATE SWITCH 
MINIMUM CLIMB RATE 
3 LIMIT IN CLIMB 
MAXIMUM RATE OF DESCENT 
INPUT FOR 5 CRUISE SCHEDULES 
(5) (6) 
CRUISE OPTION SWITCH 
0 1 
CRUISE OPT FUEL FACTOR 
1.000 1.000 
CRUISE OPT NOX FACTOR 
.000 .000 
MAXIMUM MACH NUMBER 
.8000 .0000 
CLMMIN 
CLMMAX 
CLAMIN 
CLAMAX 
NINCL 
FWF 
NCRCL 
CLDCD 
IPPCL 
ISTCL 
MAXCL 
IFAACL 
IFAADE 
NODIVE 
DIVLIM 
QLIM 
RDLIM 
IOC 
FFUEL 
FNOX 
CRMACH 
(1) 
.3000 
.9000 
0 . 
3250O, 
(2) 
.3000 
.9000 
10000. 
50000. 
(1) 
0 
1.00C 
.000 
.9000 
20 
-. ooio 
4 
.00000 
4 
3 
20 
-.0010 
1 
. ooooo 
4 2 I 
0 
0 
1 
0. FT/MIN 
.0 PSF 
-99999.0 FT/MIN 
(2) 
0 
1.000 
.000 
.9000 
(3) 
.3000 
, 0000 
0 . 
0. 
31 
-.ooio 
1 
. ooooo 
1 
0 
(3) 4 
1 .000 
.000 
. 9000 
-OUT 
MAXIMUM ALTITUDE CRALT 50000, 50000, 50000. 50000. 
0. -1. FT 
DRAG COEFFICIENT INCREMENT CRDCD .00000 .ooooo .00000 .00000 
.00000 .00000 
STORE DRAG DURING CRUISE ISTCR 1 3 3 3 
3 0 
LONG RANGE CRUISE FACTOR FLRCR 1. 000 1.000 1 . 000 i. ooc 1.000 1.000 
MINIMUM MACH NUMBER CRMM1N .7000 .7000 .3000 .7000 
.3000 .0000 
MAXIMUM LIFT COEFFICIENT CRCLMX 1.0000 1.0000 1.000C 1.0000 
1.0000 .0000 
ENGINE FEATHERING ALLOWED IFEATH 0 0 0 0 
J u 
ENGINE FRACTION REMAINING FEATHF .5000 .5000 .5000 .5000 .5000 ,5000 
CD INCREASE FOR FEATHERING CDFETH .ooooo .00000 .00000 .ooooo 
.00000 .00000 
MINIMUM CRUISE ALTITUDE HPMIN 200. 30000. 0. 35000. 
0. 1000. FT 
INCREMENT IN CRUISE WT. DCWT 1.0 LEF 
RATE OF CLIMB CEILING RCIN 100 .0 FT/MIN 
INPUT FOR DESCENT SCHEDULE 
DESCENT OPTION SWITCH IVS 0 
DESCENT LIFT COEFF. DECL .8000 
MINIMUM DESCENT MACH NO. DEMMIN .3000 
MAXIMUM DESCENT MACH NO. DEMMAX , oooo 
MINIMUM DESCENT ALTITUDE DEAMIN 0. FT 
MAXIMUM DESCENT ALTITUDE DEAMAX 0. FT 
NUMBER OF DESCENT STEPS NINDE 31 
DRAG COEFFICIENT INCREMENT DSDCD .ooooo 
STORE DRAG DURING DESCENT ISTDE 0 
RESERVE SEGMENT INPUT 
RESERVE CALC. OR CONST IRS 2 
RESERVE FUEL RESRFU .000 LBM 
FRACTION OF TRIP FUEL RESTRP .000 
MISSED APPROACH TIME TIMMAP .0 MIN 
RANGE TO ALTERNATE AIRPORT ALTRAN ,0 N MI 
RESERVE CLIMB SCHEDULE NCLRES 1 
RESERVE CRUISE SCHEDULE NCRRES 1 
START RESERVE MACH NUMBER SREMCH .3000 
END RESERVE MACH NUMBER EREMCH .3000 
START RESERVE ALTITUDE SREALT 0. FT 
END RESERVE ALTITUDE EREALT 0. FT 
RESERVE HOLDING TIME HOLDTM .0 MIN 
HOLD CRUISE SCHEDULE NCRHOL 1 
HOLD POSITION SWITCH IHOPOS 1 
CRUISE ONLY SWITCH ICRON 0 
2ND RES HOLD TIME OR FRAC THOLD .000 MIN 
THOLD CRUISE SCHEDULE NCRTH 1 
STORE DRAG COEFFICIENTS - 1 
MACH NUMBER .30000 .90000 1.00000 1.40000 
DRAG COEFFICIENT .00580 .00620 .013E 0 .02620 
STORE DRAG COEFFICIENTS 
MACH NUMBER 
DRAG COEFFICIENT 
.30000 
.00160 
. 90000 
,00160 
1.20000 1.60000 
.00470 .00530 
STORE DRAG COEFFICIENTS - 3 
MACH NUMBER .30000 .90000 .95000 1.40000 
DRAG COEFFICIENT -.00070 -.00080 -.00080 -.00120 
Nov 18 96 [ 
15:07:53 F16-FLOPS-OUT 
ft MISSION SEQUENCE DEFINITION 
START 
CLIMB 
CRUISE 
HOLD 
RELEASE 
ACCELERATE 
TURN 
MACH NUMBER ,3000 ALTITUDE 0. FT 
.7000 
1 
3 
1529.0 LB 
TURN 
TURN 
TURN 
TURN 
TURN 
RELEASE 
CLIMB 
CRUISE 
HOLD 
DESCENT 
END 
USE CLIMB SCHEDULE 
START MACH NUMBER = 
USE CRUISE SCHEDULE 
USE CRUISE SCHEDULE 
PAYLOAD WEIGHT 
TO MACH NUMBER = .9000 
START MACH NUMBER * .0000 
STORE DRAG WILL BE INCLUDED 
ARC = 360.0 DEGREES 
MACK NUMBER = .9000 
STORE DRAG WILL BE INCLUDED 
ARC = 360.0 DEGREES 
MACH NUMBER = .9000 
STORE DRAG WILL BE INCLUDED 
ARC = 360.0 DEGREES 
MACH NUMBER = .9000 
STORE DRAG WILL BE INCLUDED 
ARC = 360.0 DEGREES 
MACH NUMBER = .9000 
STORE DRAG WILL BE INCLUDED 
ARC = 360.0 DEGREES 
MACH NUMBER = .9000 
STORE DRAG WILL BE INCLUDED 
ARC = 110.0 DEGREES 
MACH NUMBER = .9000 
STORE DRAG WILL BE INCLUDED 
PAYLOAD WEIGHT = 1168.5 LB 
USE CLIMB SCHEDULE 2 
USE CRUISE SCHEDULE 4 
USE CRUISE SCHEDULE 5 
ALTITUDE = 0 . FT 
SEGMENT DISTANCE = 2 50.0 N MI 
HOLD TIME = 120.0 MIN 
AT POWER SETTING 1 
ALTITUDE = 10000. FT 
AT POWER SETTING 1 
ALTITUDE = 10000. FT 
AT POWER SETTING 1 
ALTITUDE = 10000. FT 
AT POWER SETTING 1 
ALTITUDE = 10000, FT 
AT POWER SETTING 1 
ALTITUDE = 10000. FT 
AT POWER SETTING 1 
ALTITUDE = 10000, FT 
AT POWER SETTING 1 
ALTITUDE = 10000. FT 
SEGMENT DISTANCE = 270.0 N MI 
HOLD TIME = 20.0 MIN 
MACH NUMBER .3000 ALTITUDE 
S NAMELIST SPCONIN 
INPUT FOR 5 PERFORMANCE CONSTRAINTS 
NO. ICONTP ICSTDG 
CONNZ CONPC 
CONWT CONFM CONWTA 
NEO CONAUX CONLIM 
ICONSG 
1 16 
1 .000 
1.000 
i, ooo 
1.000 
i .ooo 
3 
1 .000 
3 
i .ooo 
3 
1. 000 
3 
i .ooo 
2 
1 . 000 
.4000 
1.400 
1 . 400 
1 .400 
1.400 
1 . 400 
, 4000 
.4000 
. 000 
.000 
.000 
.000 
.000 
0. 
CONALT 
30000. 
30000. 
30000. 
30000. 
30000. 
. 800 
.900 
.900 
. 900 
1.200 
It USER-DEFINED AERODYNAMIC DATA 
DRAG DUE TO LIFT 
MACH/CL .000 .050 .100 .150 
.700 .800 ,900 1.000 1,100 1 
1.300 1.400 1.500 
.200 
200 
.300 .4 00 .500 .600 
.000 
.06690 
.200 
. 06070 
.300 
. 05790 
.400 
. 05630 
.500 
. 04 6OC 
. 600 
. 05650 
.700 
.05810 
. 800 
.06030 
.850 
.06130 
. 900 
.06560 
.950 
.07390 
1.000 
.08800 
1.050 
.09580 
1.100 
. 11250 
1 .200 
.13250 
1 .300 
.13760 
1.400 
.15070 
1 .500 
.16710 
1 . 600 
. 18820 
1.700 
9.99000 9 
1 .800 
9.99000 9 
1 . 900 
9.99000 9 
2 . 000 
.00000 
.09410 
.26300 
.00000 
.08360 
.28390 
.00000 
.08010 
.29580 
.00000 
.07800 
.30740 
.00000 
,07620 
.32010 
.00000 
,07580 
.33300 
,00000 
.07960 
.34480 
.00000 
.08440 
.36210 
.00000 
.08710 , 
.37720 
.00000 
.09200 
,41000 
.00000 
.10150 . 
9 . 99000 
.00000 
.12360 
9.99000 
,00000 
.13950 , 
9 . 99000 
,00000 
.15050 
9 .99000 
,00000 
.16670 , 
9 .99000 
,00000 
.18160 
9.99000 
.ooooo 
.20340 
9.99000 
.00000 
.22B20 , 
9 .99000 
, OOOOC 
.25780 
9 .99000 
.00000 
99000 9. 
9.99000 
. ooooo 
99000 9. 
9 .99000 
. ooooo 
99000 9, 
9.99000 
.00000 
, 00000 
.12030 
.33900 
.00000 
.11100 
.36400 
.00000 
. 10780 
.37650 
.00000 
,10620 
.38990 
.00000 
, 10590 
.40410 
.00000 
. 10810 
.41920 
- .00010 
. 11250 
.43130 
.00010 
,11830 
.44640 
.00020 
,12240 
.45920 
.00020 
. 1304C 
.51460 
.00060 
13870 
9 . 99000 
.00010 
17620 
9.99000 
.00040 
19100 
9.99000 
.00040 
19940 
9.99000 
.00000 
21240 
9 .99000 
.00060 
25220 
9 . 99000 
.00060 
29930 
9.99OO0 
.00060 
32260 
9.99000 
.00060 
33420 
9.99000 
.0OO70 
99000 9. 
9.99000 
.00070 
99000 9. 
9.99000 
,00060 
99000 9. 
9.99000 
.00050 
.00040 
. 13370 
.4160C 
.00050 
14140 
.45790 
,00050 
.14520 
.47950 
.00060 
14910 
.50190 
.00050 
15330 
. 52560 
,00050 
15860 
.55040 
.00040 
16090 
.57030 
.00060 
16320 
.59120 
.00070 
16770 
.61220 
,00080 
17950 
.72320 
.00160 
19940 
9 . 99000 
.00120 
23580 
9.99000 
.00160 
24950 
9.9900C 
.00160 
25460 
9.99000 
.00120 
26000 
9.99000 
.00200 
33350 9 
9.99000 
.00220 
38530 9 
9.99000 
.00280 
40780 9 
9.99000 
.00280 
41830 9 
9.99000 
.00290 
99000 9 
9.99000 
,00300 
99000 9 
9.99000 
,00290 
99000 9 
9.99000 
.002 80 
.00140 
16710 
.00150 
. 17890 
.00150 
.18510 
.00170 
.19150 
.00160 
19820 
. 00170 
. 21660 
.00330 
31000 
.00330 
31490 
.00340 
30980 
.00460 
99000 9 
.0059C 
99000 9 
.00650 
99000 9 
.00670 
99000 9 
.00690 
99000 9 
.00720 
99000 9 
.00720 
99000 9. 
.00310 
21050 
.00330 
22460 
.00330 
23200 
.00340 
24140 
.00340 
.25160 
.00150 
20530 
.00150 
,21170 
.00340 
26260 
.00340 
27380 
.00350 
.28580 
.00190 
.22140 
.00360 
!9630 
.00230 
.24440 
.00320 
27140 
,00310 
28620 
.00440 
32020 
.00530 
33850 
.00590 
35370 
.00620 
37300 
.00650 
38390 
.00720 
39630 
.00900 
99O0C 
.01060 
99000 
.01210 
99000 
.01280 
99000 
.01320 
99000 
.01370 
99000 
.01420 
99000 
.00810 .01650 .02850 .04470 
.00860 .01700 .02830 .04280 
.00880 .01710 .02820 .04210 
.00900 .01730 .02820 .04160 
,00900 .01740 .02810 .04120 
.00900 .01730 .02800 .04110 
.00900 .01720 .02890 .04150 
.00890 .01710 ,02800 .04230 
.00900 .01710 .02810 ,04270 
.01060 .01360 .02980 .04540 
.01180 ,02240 .03690 .05430 
.01450 .02620 .04340 .06560 
.01380 .02730 .04560 .07030 
.01540 .02830 .04860 .07760 
.01740 .03110 .05570 ,08890 
.01910 .03630 .06280 .09760 
.02200 .04330 ,06980 ,10650 
.02640 .04970 .07730 .11790 
.03010 .05530 .08400 .13270 
.03290 .06140 .09330 9.99000 
.03530 .06760 .10440 9.990O0 
.03790 .07340 .11800 9.990O0 
.00720 .01480 .04030 .07930 .13330 9.99000 
Nov 18 96 
15:07:53 F16 
9.99000 9.99000 9.99000 9.99000 9.99000 9.99000 
9.99000 9.99000 9.99000 
2.100 .00000 .00070 .00300 .00770 .01400 
9.99000 9.99000 9.99000 9.99000 9.99000 9.99O00 
9.99000 9.99000 9.99000 
.04320 .08600 .14950 9.99000 
LIFT INDEPENDENT DRAG INCLUDING WAVE DRAG, IF ANY 
ALT / MACH 
. 900 
0 . 
. 01947 
5000. 
.01947 
10000. 
.01947 
15000, 
.01960 
20000. 
. 01985 
25000. 
.02011 
30000. 
.02040 
35000. 
.02071 
40000. 
. 02112 
45000. 
.02159 
50000. 
.02208 
55000. 
.02259 
60000. 
.02313 
.000 
.950 
1.300 
.01853 
02763 
,04336 
.01880 
.02763 
.04336 
.01910 
02763 
.04336 
.01941 
02771 
. 04336 
.01975 
02796 
. 04349 
,02011 
02822 
.04373 
.02050 
02850 
.04400 
.02092 
02880 
.04429 
.02149 
02922 
.04467 
.02213 
02968 
.04510 
.02281 
03016 
.04556 
.02353 
03066 
.04603 
,02428 
03120 
. 04653 
.200 
1.000 
1,400 
.01743 
.04198 
.04368 
.01770 
.04198 
.04368 
,01800 
.04198 
.04368 
.01831 
.04202 
.04368 
,01865 
.04226 
.04379 
.01901 
.04252 
.04404 
.01940 
.04280 
.04430 
.01982 
. 0431C 
.04458 
.02039 
.04351 
.04496 
.02103 
.04396 
, 04539 
.02171 
.04444 
. 04583 
.02243 
.04494 
.04630 
. 02318 
. 04547 
,04679 
. 300 
1.050 
1. 500 
.01719 
.04422 
.04430 
.01744 
.04422 
.04430 
.01771 
.04422 
.04430 
.01800 
.04423 
.04430 
.01831 
.04447 
.04440 
.01864 
,04472 
.04464 
.01900 
,04500 
.04490 
.01939 
,04530 
.04518 
,02991 
,04570 
. 04555 
.02050 
.04615 
.04597 
.02111 
.04662 
,04641 
.02176 
.04712 
.04687 
.02245 
.04764 
.04736 
.400 
1.10C 
1.600 
.01689 
.04416 
.04561 
.01713 
04416 
.04561 
.01739 
04416 
.04561 
.01766 
04416 
.04561 
.01795 
.04437 
.04571 
.01826 
.04463 
.04595 
.01860 
. 04490 
.04620 
.01896 
,04520 
.04647 
.01946 
.04560 
. 04685 
.02001 
.04604 
,04726 
.02059 
.04651 
.04769 
.02120 
.04700 
.04815 
.02184 
. 04752 
.04863 
. 500 
1. 200 
1.700 
,01677 
.04381 
.04611 
.01700 
.04381 
.04611 
,01724 
.04381 
.04611 
.01750 
.04381 
.04611 
.01778 
.04398 
.04621 
,01808 
,04423 
.04645 
,01840 
,04450 
.04670 
.01875 
.04479 
.04697 
. 01922 
,04518 
,04734 
.01974 
.04562 
.04775 
. 02029 
.04608 
.04817 
.02088 
.04656 
,04862 
.02149 
.04707 
,04910 
.600 
1.800 
,01691 
.04621 
.01705 
.04621 
,01728 
.04621 
.01753 
.04621 
.01780 
. 04632 
.01809 
. 04655 
.01840 
.04 680 
,01873 
. 04707 
.01919 
.04743 
.01969 
,04784 
, 02022 
.04826 
,02078 
. 0487C 
.02137 
.700 
1 . 900 
.01745 
.04539 
.01745 
.04589 
, 01762 
.04589 
. 01786 
.04589 
.01812 
. 04602 
.01840 
. 04625 
,01870 
.04650 
.01902 
.04677 
, 01946 
.04713 
. 01995 
.04752 
.02046 
.04794 
.02101 
.04833 
.02158 
.800 
2 . 000 
.01833 
.04526 
.01833 
.04526 
.01835 
.04526 
.01858 
.04526 
.01384 
. 04543 
.01911 
.04566 
.01940 
. 04590 
.01971 
.04616 
.02014 
.04652 
,02062 
.04691 
.02112 
.04733 
.02164 
.04776 
.02220 
,850 
.01881 
. 01881 
.01881 
.01899 
.01924 
.01951 
. 01980 
.02011 
.02053 
,02100 
,02150 
.02201 
.02256 
.04917 .04884 .04822 
(TITLE, BEGIN OUTPUT OF RESULTS 
flfic Air Superiority Mission, 2AIM-9, 2AIM-120, External Fuel 
» CRUISE OPTIMIZATION RESULTS 
SUMMARY DATA FOR CRUISE SCHEDULE 1 
WEIGHT ALTITUDE THRUST FUEL SFC MACH VELOCITY SPECIFI 
C RATE OF CL L/D ENGINES NOX 
AVAILABLE REQUIRED FLOW NUMBER RANGE 
CLIMB OPERATING RATE 
-OUT 
17400. 49203. 2518 . 1940 . 1840. .9484 .8610 493 9 . 2684 
+ 0 1661.6 .4416 S 97 1 0 .00 
18000. 49316, 2514 . 2013. 1906 . .9466 .8660 496 7 .2606 
0 1397.6 .4541 8 .94 1 0 .00 
18600. 48676. 2600. 2079 , 1964. . 9447 ,8668 497 2 .2531 
+ 0 1410.0 .4542 8 95 1 0 .00 
19200, 47960. 2694 . 2143. 2020 . .9427 .8666 497 0 .2460 
+• 4 1445.4 .4533 B 96 1 0 .00 
19800. 47263. 2786 , 2206, 2076. , 9408 ,8663 496 9 ,2393 
+ 8 1472.4 ,4525 6 97 1 0 .00 
20400, 46587. 2874 . 2270. 2131. .9389 .8660 496 7 .2330 
+ 8 1491 .0 .4517 8 99 1 0 .00 
21000, 45932. 2960. 2333 , 2186, . 9371 , 8657 496 S . 2271 
2 1502.2 .4509 9 00 1 0 .00 21600. 45295. 3044 . 2396. 2241 . .9354 .8654 496 4 .2214 + 7 1507.1 ,4501 9 01 1 0 .00 22200, 44630, 3143 . 2458. 2295 . .9336 . 8648 496 0 .2161 
+ 1 1548.3 .4487 9 03 1 0 .00 
22800. 44012. 3244. 2521. 2350. .9320 .8645 495 6 .2110 
+ 1 1592.6 .4478 9 04 1 0 . 00 
23400. 43473. 3334 . 2585 . 2406 . . 9305 , 8646 495 9 .2061 
+ 6 1608.0 .4477 9 05 1 0 .00 
24000. 42927. 3425 . 2648 . 2460. .9290 .8645 495 8 .2015 
+ 3 1623.9 ,4475 9 06 1 0 . 00 
24600, 42402. 3512 . 2712 . 2516. . 9276 .8645 495 8 . 1971 
+ 3 1632.5 .4473 9 07 1 0 .00 
25200. 41882. 3598 , 2775 . 2570 . .9262 ,8643 495 8 .1928 
+ 8 1638.8 .4471 9 08 1 0 .00 
25800. 41377, 3681. 2838. 2625. . 9249 .8643 495 7 .1888 
+• 4 1640.4 .4469 9 09 1 0 .00 
26400, 40879. 3764 . 2901 . 2680 . . 9236 .8642 495 7 . 1849 
+ 7 1639.4 .4466 9 10 1 0 .00 
27000. 40393. 3844 , 2964 . 2734 . , 9224 , 8641 495 6 . 1812 
5 1635.0 .4464 9 11 1 0 ,0C 
27600. 40039. 3908 . 3032 . 2795, .9216 .8657 496 6 . 1776 
9 1595.7 .4469 9 10 1 0 .00 
28200. 40000, 3917 , 3100. 2853 . . 9202 .8666 497 0 .1742 
+ 3 1457.9 .4549 9 10 1 0 .00 
28800 , 39945. 3938. 3174 . 2920 . .9197 .8697 498 8 .1708 
+ 4 1339,5 .4600 9 07 1 0 .00 
29400. 39535. 4026. 3240. 2980. , 9196 .8706 499 3 .1675 
4 7 1350.7 .4596 9 07 1 0 .00 
30000. 39026. 4128 . 3300 . 3033 , .9190 .8695 498 7 .1644 
+ 2 1393.0 .4587 9 09 1 0 .00 
30600. 38592. 4218. 3364 . 3090. .9186 .8696 498 8 .1613 
t 9 1409 , 3 .4582 9 10 1 0 .00 
31200. 38127. 4312 , 3425 . 3145 . ,9181 . 869C 493 4 . 1584 
+ 8 1434 . 8 . 4576 9 11 1 0 .00 
31800. 37705. 4400. 3489 . 3202 . . 9177 .8683 498 4 ,15S6 
7 1445.9 .4571 9 12 1 0 .00 
32400. 37265. 4489 . 3550 . 3256 . .9172 . 8684 498 1 .1529 
+ 7 1461.4 . 4565 9 13 1 0 . 00 
33000. 36860. 4573 , 3613 . 3313 . , 9168 . 86B4 498 1 .1503 
+ 6 1466.4 .4561 9 13 1 0 ,00 
33600. 35000. 4937 . 3654 , 3353 , . 9177 . 8627 497 4 . 14B3 
+ 5 1924.8 . 4305 9 20 1 0 .00 
SUMMARY DATA FOR CRUISE SCHEDULE 2 
WEIGHT ALTITUDE THRUST FUEL SFC MACH VELOCITY SPECIFI 
+ C RATE OF CL L/D ENGINES NOX 
AVAILABLE REQUIRED FLOW NUMBER RANGE 
+ CLIMB OPERATING RATE 
17400. 47885. 2698. 1654. 1609. .9727 .8640 495.6 .3079 
+ 9 3011.5 .4118 10,52 1.0 .00 
Nov 18 96 
15:07:53 F16-FLOPS-OUT 
18000. 47527. 2752 . 1715. 1661. . 96B8 .8666 497 1 . 2992 18600. 50000. 2373. 1828. 1726 . . 9442 ,8413 482 6 ,2796 
+ 4 2899.8 4162 10 50 1 0 . 00 + 2 1432 .0 .5136 10 18 1 0 .00 
18600, 46869. 2842 . 1771 , 1712 . .9666 .8680 497 9 .2908 19200. 50000, 2390. 1899 . 1793. ,9440 .8498 487. 4 .2718 
+ 3 2903.0 4154 10 50 1 0 .00 + 9 1262.5 , 5198 10 11 1 0 .00 
19200. 46211. 2 926. 1824. 1758 . .9638 .8669 497 3 .2829 19800. 50000. 2390 , 1981, 1862. .9396 .8500 487 5 .2618 
4 2 2892.4 4166 10 53 1 0 . 00 4 6 1020.2 .5357 9 99 1 0 .00 
19800. 45558. 3016 . 1879 . 1808 , . 9619 .8681 497 9 . 2754 20400, 50000. 2391. 2068 . 1934. .9353 .8500 437. 5 .2521 
4 : 2894 .4 4152 10 54 1 0 .00 4 0 781.4 .5519 9 87 1 0 .00 
20400. 44925. 3104. 1934 . 1857. .9600 .8688 498 3 .2683 21000. 50000. 2397 . 2154. 2010 , .9332 .8530 489 3 .2434 
4 B 2893.8 4144 10 55 1 0 .00 4 0 572 .4 . 5641 9 75 1 0 .00 
21000. 44398. 3190. 1988. 1904 . .9577 .8682 498 0 .2615 21600. 50000. 2413 . 2239. 2097 . .9369 .8608 493 7 .2353 
4 1 2887.3 4165 10 56 1 0 ,00 + 9 402 .6 .5698 9 65 1 0 .00 
21600. 43872. 3279 . 2044 , 1953. . 9559 . 8689 498 4 .2551 22200. 50000. 2420. 2330 . 2188 , .9391 .8643 495 7 .2265 
+ 2 2887.6 4171 10 57 1 0 .00 4 7 203 . 1 ,5809 9 53 1 0 .00 
22200. 43348. 3368 . 2099 . 2003 . .9542 .8694 498 7 .2489 22800. 49881. 2456. 2411, 2274 . .9429 , 8744 501 5 .2205 
4 9 2887 .3 4176 10 58 1 0 .00 4 7 100 .0 .5796 9 45 1 0 .00 
22800. 42825, 3456. 2154 , 2052 . .9526 .8698 498 9 ,2431 23400, 49670. 2538. 2493 . 2372 . ,9516 .8999 516 2 .2175 
4 6 2886.3 4179 10 59 1 0 .00 4 9 100.0 ,5559 9 39 1 0 .00 
.2124 23400. 42304, 3544. 2209 . 2100. .9510 .8701 499 1 .2376 24000. 49186. 2603 . 2557 . 2430. .9501 . 9000 516 2 
4 2 28S4.8 4180 10 60 1 0 .00 4 5 100. 0 .5571 9 38 1 0 .00 
.2075 24000. 41784. 3631. 2263. 2148 , .9495 .8703 499 2 .2323 24600. 48705, 2669 , 2622. 2487 . .9487 .9000 516 2 
+ 5 2882 . 5 4180 10 61 1 0 .00 4 7 100.0 .5580 9 38 1 0 .00 
24600. 412 67 . 3718 . 2317 . 2196 . .9480 . 8704 499 3 .2273 25200. 48228. 2733 . 2685 . 2544 . .9473 .9000 516 2 .2029 
+ 2 2879.6 4179 10 62 1 0 , 00 4 5 100.0 .5587 9 39 1 0 ,00 
25200. 40761. 3802 . 2371 , 2244 . . 9465 .8705 499 3 .2225 25800. 47755. 2797 . 2748 . 2600 . ,9460 .9000 516 7 .1985 
+ 2 2872 . 8 4177 10 63 1 0 .00 + 6 100.0 .5592 9 39 1 0 .00 
. 1944 25800. 40247. 3888. 2424 . 2291. . 9451 .8706 499 3 .2179 26400. 47286. 2861. 2811. 2655, . 9448 . 9000 516 2 
4 4 2869.5 4172 10 64 1 0 .00 + 0 100.0 .5595 9 39 1 0 ,00 
26400. 39782. 3975 , 2478 . 2339 . , 9441 , 8706 499 3 . 2134 27000. 46320. 2924. 2873. 2711. .9437 .9000 516 2 .1904 
4 4 2866.6 4175 10 65 1 0 .00 4 4 100. 0 . 5596 9 40 1 0 , 00 
27000. 39362. 4062 . 2532 . 2339. .9433 .8706 499 3 ,2090 27600. 46359. 2987. 2934 , 2765 . .9426 . 9000 516 2 . 1866 
+ 4 2864.3 4185 10 66 1 0 .00 4 7 100.0 , 5596 9 41 1 0 .00 
.1830 27600. 38945. 4148 . 2587 . 2438 . .9425 .8707 499 4 .2048 28200. 45901. 3049 , 2995 . 2820. . 9415 .9000 516 2 
4 3 2861.3 4193 10 67 1 0 .00 4 1 100.0 .5593 9 42 1 0 .00 
,1796 28200. 38525. 4234 , 2640 . 2485 . .9416 . 8701 499 0 .2008 28800. 45447. 3110. 3055 , 2874 . . 9405 , 9000 516 2 
+ 0 2856.7 4204 10 68 1 0 .00 4 4 100.0 .5590 9 43 1 0 .00 
28800. 38135. 4314 . 2694. 2534. .9406 .8699 499 0 .1969 29400. 44997. 3172 . 3115 . 2327 . , 9396 .9000 516 2 ,1763 
4 2 2842.6 4216 10 69 1 0 ,00 + 6 100.0 .5585 9 44 1 0 .00 
29400. 37767. 4391. 2749 , 2584 . , 9398 .8703 499 2 .1932 30000, 44612. 3237. 3180 . 2984 . ,9385 .9000 516 2 , 1729 
+ 0 2823.4 4225 10 69 1 0 .00 4 9 100. 0 .5594 9 44 1 0 ,00 .1697 
30000. 37357. 4477 . 2804. 2633. .9392 . 8706 499 4 .1896 30600. 44229. 3302 . 3244 , 3041, .9375 .9000 516 2 
+ 3 2821.4 4224 10 70 1 0 .00 4 6 100.C .5603 9 43 1 0 .00 
.1666 30600. 36944. 4564 . 2858. 2683 . .9387 .8709 499 5 , 1862 31200. 43848. 3367 . 3307 . 3097 . .9365 . 9000 516 2 
4 0 2820.4 4222 10 71 1 0 .00 4 8 100.0 .5609 9 43 1 0 .00 
.1637 31200. 35038. 4931. 2871 . 2716. .9461 . 8632 497 6 ,1831 31800. 43470, 3431 , 3370. 3153. .9355 .9000 516 2 
4 9 3327.7 4000 10 87 1 0 .00 + 2 100.0 . 5615 9 44 1 0 .00 
.1608 31800. 35000. 4940. 2929 . 2762 . .9428 . 8635 497 9 .1802 32400. 43094, 3495. 3433 . 3209. .9346 . 9000 516 2 
+ 7 3188.3 4067 10 86 1 0 ,00 4 8 100 .0 .5619 9 44 1 0 .00 
32400. 35000. 4940. 2988. 2807 , ,9332 .8635 497 9 . 1773 33000, 42720. 3559 . 3495 , 3264 . ,9338 .9000 516 2 .1581 
4 8 3037 , 1 4144 10 84 1 0 .00 + 5 100.0 .5621 9 44 1 0 .00 
.1555 33000. 3 5000. 4940 . 3049 . 2853 . . 9356 . 8635 497 9 .1745 33600. 42349, 3622 . 3557 . 3319. .9330 . 9000 516 2 
4 2 2889,3 
33600. 
4221 
34909. 
10 82 
4976. 
1 0 
3116, 
.00 
2913 . ,9349 .8672 500 2 .1717 
4 4 100 .0 ,5623 9 45 1 0 .00 
+ 0 2804.5 4243 10 78 1 0 .00 
SUMMARY DATA FOR CRUISE SCHEDULE 4 
SUMMARY DATA FOR CRUISE SCHEDULE 3 
WEIGHT ALTITUDE THRUST 
2 RATE OF CL L/D ENGINES NOX 
AVAILABLE REQUIRED 
CLIMB OPERATING RATE 
WEIGHT ALTITUDE 
RATE OF CL 
FUEL 
- 6 
t 3 
1740O. 
1740.0 
18000. 
1585.8 
50000. 
.5059 
50000. 
.5097 
2329 . 
10.28 
2351 . 
10 .23 
1693 . 
FUEL 
FLOW 
1596 . 
1.0 .00 
1760. 
.9426 
. 9435 
MACH VELOCITY 
NUMBER 
.8200 470.3 
.8309 476.6 
SPECIFI 
RANGE 
.2946 
. 2870 
1,0 
+ 9 
* 3 
CLIMB 
17400. 
3011.5 
18000. 
2899.8 
13600. 
2903.0 
47885 
.4118 
47527 
.4162 
46869 
. 4154 
THRUST 
L/D ENGINES NOX 
AVAILABLE REQUIRED FLOW 
OPERATING RATE 
2698. 1654. 1609. 
10.52 1.0 .00 
2752. 1715. 1661. 
10.50 1.0 .00 
2842. 1771. 1712. 
10.50 1.0 .00 
.9727 
. 9638 
.9666 
MACH VELOCITY SPECIFI 
NUMBER RANGE 
.8640 495.6 .3079 
.8666 497,1 .2992 
.8680 497.9 .2908 
Nov 1896 
15:07:53 • 
19200. 46211. 2926 . 1824 . 1758 
2 2892 . 4 4166 10 53 1 0 .00 
19800. 45558. 3016. 1879 . 1808 
5 2894.4 4152 10 54 1 0 .00 
20400. 44925. 3104 . 1934 . 1857 
00 2893.8 4144 10 55 1 0 .00 
21000. 44398. 3190. 1988 . 1904 
7 2887.3 4165 10 56 1 0 .00 
21600. 43872 . 3279 . 2044 . 1953 
2 28B7.6 4171 10 57 1 0 ,00 
22200. 43348. 3368 , 2099 . 2003 
9 2887.3 4176 10 58 1 0 .00 
22800. 42825. 3456. 2154 . 2052 
6 2886.3 4179 10 59 1 0 .00 
23400. 42304, 3544. 2209. 2100 
2 2884 . 8 4180 10 60 1 0 .00 
24000. 41784. 3631 . 2263. 2148 
5 2882.5 4180 10 61 1 0 .00 
24600. 41267. 3718 . 2317 . 2196 
2 2879.6 4179 10 62 1 0 .00 
25200. 40761. 3 802 . 2371. 2244 
2 2872.8 4177 10 63 1 0 .00 
25800, 40247. 3888 , 2424 . 2291 
4 2869.5 4172 10 64 1 0 .00 26400. 39782. 3975. 2478. 2339 4 2866.6 4175 10 65 1 0 .00 
27000. 39362. 4062 . 2532 . 2339 
4 2864.3 4185 10 66 1 0 .00 27600. 38945. 4148 , 2587. 2438 3 2861.3 4193 10 67 1 0 . 00 
28200. 38S25. 4234 . 2640. 2485 
0 2856.7 4204 10 68 1 0 ,00 
28800. 38135. 4314. 2694 , 2534 
2 2842 . 6 4216 10 69 1 0 . 00 
29400. 37767. 4391 , 2749 . 2584 
0 2823.4 4225 10 69 1 0 .00 
30000, 37357. 4477 . 2804. 2633 
3 2821.4 4224 10 70 1 0 .00 
30600. 36944, 4564 . 2858 . 2683 
0 2820.4 4222 10 71 1 0 , 00 
31200. 35039. 4931 . 2871. 2717 
9 3327.5 4000 10 37 1 0 .00 31800. 35000. 4940. 2929 . 2762 9 
3188 .1 
4068 10 86 1 0 .00 
32400. 35000. 4940 . 2988 . 2807 
S 3036.9 4144 10 84 1 0 ,00 
33000. 35000. 4940. 3049 . 2853 
2 2889.1 4221 10 82 1 0 .00 
33600. 35000. 4952 . 3117 . 2911 
8 2763 . 6 42 65 10 78 1 0 . 00 
SUMMARY DATA FOR CRUISE SCHEDULE 5 
WEIGHT ALTITUDE 
RATE OF CL 
CLIMB 
THRUST 
L/D ENGINES NOX 
AVAILABLE REQUIRED 
OPERATING RATE 
17400. 
31273 .4 
18000, 
30070.4 
18600. 
28950.7 
19200. 
27916.5 
.1095 
.1141 
.1232 
16257. 2669. 
6.52 1.0 .00 
16225. 2663. 
6.76 1.0 .00 
16194. 2658. 
7.00 1.0 .00 
16168. 2656. 
7.23 1.0 .00 
FUEL 
FLOW 
3019, 
D 
3014. 
3010. 
3 
3008. 
.9638 
. 9619 
. 9600 
.9577 
.9559 
, 9542 
.9526 
. 951C 
. 9495 
.9480 
.9465 
.9451 
.9441 
.9433 
, 9425 
.9416 
. 9406 
.9398 
.9392 
. 9387 
. 9461 
.9428 
.9392 
.9356 
.9338 
SFC 
1 .1311 
1.1319 
1.1325 
1.1327 
. 8669 
.3681 
.8688 
, 8682 
.8689 
. 8694 
,8698 
.8701 
. 8703 
.8704 
.8705 
. 8706 
,8706 
. 8706 
. 8707 
.8701 
,8699 
.8703 
.3706 
.8709 
.8633 
.3634 
. 8634 
.8634 
.3668 
Fl6 FLOPS-OUT 
497 .3 
497 . 9 
498.3 
498.0 
498 . 4 
498.7 
498 .9 
499 .1 
499.2 
499.3 
499 .3 
499 .3 
499 .3 
499 .3 
499 .4 
499.0 
499 . 0 
499 .2 
499 ,4 
499 . 5 
497 . 6 
497 . 8 
497 , 8 
497 .8 
499 . 8 
.2829 
,2754 
.2683 
.2615 
.2551 
,2489 
. 2431 
.2376 
, 2323 
. 2273 
.2225 
.2179 
.2134 
.2090 
.2048 
.2008 
.1969 
. 1932 
.1896 
.1862 
.1831 
.1802 
.1773 
.1745 
.1716 
MACH VELOCITY 
NUMBER 
.5978 
.5958 
.5938 
.5922 
395.5 
394 . 1 
392.8 
391.7 
SPECIFI 
RANGE 
, 1309 
.1307 
.1305 
.1302 
+ 1 
* 0 
19800. 
+ 7 26957,7 
20400. 
+ 9 26060.5 
21000. 
+ 8 25219.7 
21600. 
+ 4 24431.0 
22200. 
+ 8 23690.3 
22800, 
+ 0 22994,0 
23400. 
22339.4 
24000. 
21732.0 
24600. 
* 6 21159.9 
25200. 
+ 0 20619.7 
25800. 
+ 3 20110.1 
26400. 
+ 3 19627.4 
27000. 
+ 3 19171.4 
27600. 
+ 1 18740.2 
28200. 
*• 7 18332 .3 
28800 , 
+ 4 17946.2 
29400. 
* 9 17580.5 
30000. 
+ 4 17233.9 
30600. 
+ 8 16905.2 
31200. 
+ 5 16594.3 
31800, 
t 2 16294.7 
32400. 
+ 9 15993.6 
33000. 
* 6 15716.3 
33600. 
+ 4 15447.0 
. 1321 
. 1366 
0. 
,1410 
.1454 
.1583 
.1623 
.1703 
. 1742 
0 . 
.1779 
.1816 
.1887 
.1921 
0 . 
. 1954 
.1986 
.2017 
0. 
. 2045 
.2110 
0. 
.2140 
16145 
7.45 
16124 
7 .67 
16105 
7 ,89 
16087 
8.10 
16072 
8.30 
16058 
8.50 
16048 
8.68 
16042 
8,35 
16039 
9 .01 
1 6037 
9.16 
16038 
9.31 
16040 
9 . 44 
16045 
9.57 
16051 
9 .70 
16060 
9.81 
16071 
9 .92 
16083 
10.02 
16098 
10,11 
16115 
10.20 
16134 
10.28 
16152 
10.37 
16168 
10.45 
16185 
10 .53 
16204 
10.60 
2657 . 
1.0 
2659 . 
1.0 
2663. 
1.0 
2668, 
1.0 
2675 . 
1.0 
2684 . 
1.0 
2697 . 
1.0 
2713. 
1.0 
2731. 
1.0 
2751. 
1.0 
2795 . 
1.0 
2820. 
1.0 
2846 . 
1 .0 
2903 , 
2934. 
1.0 
2966 . 
1.0 
3000. 
1.0 3034, 1.0 
3067 . 
1.0 3100. 1.0 
3135 . 
1 . 0 
3169 . 
1.0 
3009, 
3011. 
.00 
3014 , 
, 00 
3019 , 
.00 
3024. 
.00 
3031. 
.00 
3042. 
.00 
3055 . 
3085. 
.00 
3102 . 
.00 
3120. 
. 00 
3139 . 
,00 
3160 . 
.00 
3182 . 
,00 
3205 . 
.00 
3229. 
.00 
3255 . 
.00 
3282 . 
.00 
3309 . 
3336. 
.00 
3362 . 
,00 
3390. 
.00 
3418 . 
. 00 
1.1326 
1 .1324 
1.1320 
1.1314 
1.1305 
1.1295 
1.1279 
1.1259 
1.1237 
1.1213 
1.1187 
1.1160 
1.1131 
1.1102 
1.1071 
1.1039 
1 .1007 
1 .0974 
1.0940 
1.0907 
1.0876 
1 .0845 
1.0815 
1,0784 
CRUISE SCHEDULE RANGE AND TIME SUMMARY 
RANGE -2- TIME 
[N.MI.I (HR) 
.5907 
, 5894 
.5882 
. 587C 
.5860 
,5852 
.5845 
. 5842 
,5839 
.5838 
.5839 
.5840 
.5843 
.5847 
. 5853 
.5860 
.5868 
.5877 
. 5888 
.5900 
.5912 
.5922 
.5933 
.5944 
390.8 
389.9 
389.1 
3S8 ,3 
387 .7 
387.1 
386.6 
386.4 
386.3 
386.2 
386,2 
386.3 
386.5 386 8 
387.2 
337.6 
388.1 
338 .8 
389. 5 
390.3 
391.0 
391.7 
392 .4 
393.2 
WEIGHT 
-4- TIME 
(POUNDS) 
(HR) 
33600. 
.00 
33300. 
. 10 
33000. 
,21 
32700. 
.31 
32400. 
.42 
32100. 
RANGE -1- TIME 
RANGE -5- TIME 
(N.MI.) (HR] (N.MI.) 
. 0 
.0 
44 .7 
34 . 6 
89.6 
69.2 
134.9 
104.0 
180. 6 
138 . 9 
226.7 
(HR) 
. 00 
.00 
,09 
.09 
, IS 
,18 
.27 
. 26 
.36 
.35 
.46 
.0 
51.7 
103 .9 
156.4 
209.4 
262 .9 
. 00 
.10 
.21 
.31 
. 42 
.53 
RANGE -3-
[N.MI.) 
.0 
46 .9 
94 , 1 
141 .8 
189 . 8 
238 .3 
TIME 
(HR) 
.00 
.09 
.18 
.27 
.37 
,46 
1298 . 1294 
. 1290 
.1286 
,1281 
.1277 
.1271 
.1265 
.1258 
. 1252 
.1245 
.1238 
, 1231 . 1224 
. 1216 
. 1209 
, 1201 
.1194 
.1186 
. 1179 
. 1172 
.1164 
.1157 
,1150 
RANGE 
(N.MI.) 
. 0 
51 .7 
103.9 
156.4 
209 .4 
262 . 8 
F16-FL0PS-0UT 
+ S3 
3130D. 
173 .9 
273 2 
44 
.=5 316 ™ 64 287 2 56 116 1 
21900. 
4.S4 
2092 
1428.2 
7 4.21 
3.63 
2415 4 4.34 JRCO 6 4 . 28 2415.4 
4 . 
< IB'IU . 
209.0 
320 I 
53 
. 64 371 0 74 336 5 65 371 0 h 
111,0V . 
4.99 
2154, 
1466.A 
i 4,34 
3.73 
2491 5 4 .99 2270 . 5 4 . 42 243 1 .5 
4 .74 
31200. 
244 .3 
367 4 
62 
. 71 425 8 85 386 3 75 425 7 4 
:• .3 :•! . 
5.IS 
2225 
1505 .4 
7 4 . 48 
3 . 88 
1 • - " 5 .15 2341 .7 4 . 57 .:- . 3.5 
4- . B£ 
3Q9QQ . 
279.6 
415 2 .83 440 9 97 436 5 85 480 9 * 
21000. 
5 .30 
2253 . 
1544.1 
4 4 . 62 
3.99 
2646 5 5 .30 2414 . 1 4 , 72 2 -746. 5 
+ . 37 .7 7 SO 20700. 2162 0 4 .75 2725 4 5 . 46 7 77 . 3 4 . 87 277,5 . 4 
30600. 463 4 . 73 536 6 1 08 487 2 94 536 6 5 .46 1582.8 4,08 
4 1. OB 35 . f 90 20 ; ). 2431 . 5 4.89 2805 4 5 . 62 2562 .7 5 ,02 2B0S.4 
30300. • . 2 0 1, 01 592 7 1 19 538 4 1 04 S92 7 + 5.62 1621.7 4 . IB 
+ 1.IS JS6.2 99 20100. 2501. 7 5.04 2886 5 5. 79 2 63 9 \ 5 . 18 2886,5 
30000. 561 1 1.13 649 3 1 30 590 0 1 14 649 3 + 5.79 1640 .5 4.28 
1 1.30 4 2.7 . R 1 OS 15300. 2573 5 . 18 2968 6 5.95 2 7 7 7 .9 5. 34 2968,6 
23100. •310 7 1 .23 706 5 1 42 642 2 1 24 706 5 + 5 .95 1699.5 4 .38 
+ 1.42 457 . 9 1 17 19500. 2645. 5 5.32 3051 7 6 .12 2796 .2 30 3051.7 
291D0. 660 7 1.33 764 2 1 53 8 1 35 7 64 1 6 .12 1738.5 « IB 
1 . 53 493 .9 1 26 1 9.7 00. 271" 7 5 .47 3116 0 6.29 2 H77 .0 5 - 7 V; 3136.0 
2910U . 7] 1 2 1 .43 822 4 1 65 748 0 1 45 822 4 + 6.29 1777,5 4 . 38 
+ 1.45 530 . 0 1 3 7 18900. 7.793 . 2 5 . 62 3SJ
 7 
5 6 ,46 2959 .1 5 . 83 3221 ,5 
24800. 762 2 1 . 53 BB1 2 1 77 801 6 1 •3 881 2 4 6 Al 1316.6 4 . 68 
4 1 .77 
2F?50fv 
566 . 2 
B13 7 
75 
I .63 940 5 '••I ••) 855 8 1 66 940 5 # 
136QO. 
6 . S3 
2463 
14S5.7 
5 5 .77 
4 .73 
3303 2 6. 63 3042 . 4 8 . 3308.1 
4 1.6* 602 . 6 1 54 183(10. 2945 . 0 5.93 3396 0 7.^7 3126 .8 * • I 7 3396 . 0 
B65 8 1 .74 1000 S 2 01 910 1 7 b 10 00 5 + 6 .41 1394.9 4.BB 
4 2 .01 639 . Q 64 18000. 3022 . 6 6.03 3485 1 r 70 lilt . 3 7 34P5.1 
2 7 900 918 1.84 7i J 2 . j 9B5 1,3 1061 0 6.99 1934.1 4 ,97 
4 a . 13 675 . 6 1 7 3 .: 7" -10. 3101 . 4 6 .24 3575 6 7 . 17 3299 .0 6 . 54 3175.6 
27600. 971 3 1 .95 : ! 72 2 2 25 1021 4 1 9B 1122 2 + 7 .17 ii n. 3 5,07 
-> 2 .25 712.2 1 63 17400. 3141 . 3 6.40 3667 3 7 .36 3386 . 8 6 7 3 3667 .3 
27300. 102 4 9 2.06 11 83 9 2 37 1077 6 2 09 ..7 73 9 4 7.36 2012 .6 5 .17 
4 2.37 749. D . 92 
. 00 27000. 1079 0 2.17 1246 3 2 50 1134 5 2 20 1246 * ITERATION 1 — f ANGE - 328 .025 FOR GROSS WEIGHT = 32974 
t 2.50 
26700. 
7B5.9 
11 jj 6 
2 02 
2 .28 1309 4 7 2 1191 9 2 31 7 JLLA 4 
+ 2 .63 322 .9 2 11 S CRUISE OPTIMIZAT[[ RESULTS 
26400. 11BB 9 2 .39 1373 1 2 75 1243 f 2 42 I 777 1 
4 2 . 75 B6.0-0 2 2 7 
26100. 124 4 6 2.50 1437 4 2 HO 3 306 5 2 53 1437 4 SUMMARY DATA FOR CRUISE SCHEH1LE 1 
+ 2.HS B97 . 2 2 71 
25BO0. 1301 N 2 ,61 1502 5 3 01 13 67 J 2 65 1502 5 WEIGHT ALTITUDE THKUST FUEL SFC MACH VELOCITY SPECIPI 
3.01 934 .5 40 4 c RATE OF CL L/D EMC 1NES NOX 
2 5500. 7 357 9 2 . 72 I3T>a 2 3 14 1427 7 2 77 156R 2 AVAILABLE REQUIRED FLOW RANGE 
+ 3,14 971 . 9 2 50 + CLIMB OPERATING KATE 
25Z0D. 1415 5 2 ..35 1634 6 3 28 1488 2 2 6 a 1634 6 
. 265£ 4 3 2B 101(9 . 1 2 60 17BOO. 43'7(i3 . 2552 . 1961. 1859 . .9477 .3610 493 8 
24PDO. 14~3 7 2 . '16 :. 7 N'. 7 3 41 1549 5 3 00 1701 7 + 9 1677.3 .4411 8.97 1.0 .00 
3.41 1047.0 2 7 9 1J400. 2578 . 2056. : '41. . 9452 , 8659 496 7 • 
: • OO. 1532 5 3 . 08 1769 5 3 55 1611 4 3 12 1769 5 + 5 1427.5 . 4535 8 . 95 1,0 .00 
.24':') 4 3 . 5 10S4.7 2 79 19: 0j, 47*43 2696 . 2143 . 2020. . 9427 . S664 497 0 
24300. 1591 9 3 . 20 1838 3 68 1674 0 3 24 ] 9.3 T 1 4 4 1451.0 .757 8.96 7 . ,7 .00 
4 3 .68 • . 32.5 2 HO 20OOO. 47024. 2817 . 2227 , 2094 . .9403 .8660 196 7 . 2372 
24000. 7 672 1 3 . 32 1907 4 3 32 ',' • 7' 4 3 37 1907 4 4 4 1483 .2 .4521 8 . 98 1 . f1 . (J I-
4 1.B2 11 SO.4 2 95 20400. 46119 2 7-7. 2322 . 2148 . . 937 •• ,3657 496 7 .2290 
217i ). 1712 9 3 45 1977 5 3 96 1401 5 3 49 1977 5 4 7 1502.2 .4510 9 .00 1.0 .01 
4 3.96 119».4 3 09 . * 3, 45246. 2 3 9 6. 2241 . , 9351 .8653 496 3 . z 2 I 4 
234G0. j 774 4 3 . 57 2C43 4 11 1366 4 3 62 7:7/1° 4 4 7 1509.9 . 4500 9-01 1 . 0 . 00 
+ 4 .11 1236.5 3 13 224DO. tt 3 3175 . 2480 . 2 3 14 . .930. . 8648 196 0 .277; 
23;oo. 1B16 6 3 . £9 2120 1 4 7 ': 1931 9 3 74 2120 1 4 e 17- l .4436 9 . 03 1 . 7 . 00 
4 4,25 127 4.7 3 213 23200. 43702. 3297. 2565. 2388. .9310 .4648 496 I . 7 077 
22600. 1399 3 . ii2 2192 6 4 3S 1997 3 3 87 ,7 .. 7 E 4 5 15:75 .5 .4486 9.05 1 . .00 
4 4.3i 1113 . ( 3 33 2.400O. •' 7G ' , 3116 , 2649. 2 • I . ,9290 .8647 496 0 . 2015 
22400. 19£3 3.95 2 2 6 6 0 4 54 2(164 1 4 U ! 1266 0 4 3 1605.5 .44 64 9 . 00 1. c 
4 4 ,54 13 51 7 •' 43 24900. 42230 3532 . :-. 'V!. 2411. . 9271 . 8646 495 .1954 
222DD. 2027,6 4 OS 2340 4 69 2131 9 t 1 1 2340 2 +• 1(17,7 . 4432 9.07 . J 
4 . US? .7 5 5B 256D0. 41593. 3645 . 2 sua. i. .9253 . 8645 495 S .1907 
Nov 18 96 
15:07:53 F16-FLOPS-OUT 
7 1623.1 .4479 9 .08 1 ,0 .00 4 3 2876.0 .4165 10 63 1 .0 .00 
26400. 40934. 3755, 2902 2680. .9236 . 8644 495 .8 .1849 26400. 39782. 3978 . 2480 2342. . 9444 . 8715 499 9 .2134 
1 1622.5 . 4475 9 .10 1 .0 .00 4 3 2871.9 .4166 10 .64 1 .0 .00 27200 . 40287. 3862 . 2986 2753 . . 9219 .8642 495 .7 . 1800 27200. 39288. 4073 . 2549 2401. ,9421 .8692 498 5 . 2076 5 1616.5 .4472 9 ,11 1 . 0 .00 4 2 2828.5 . 4215 10 67 1 .0 .00 28000. 40000. 3914 . 3076 2831. .9204 .8656 496 . 5 .1753 28000. 38667, 4205. 2622 2470. . 9419 . 8704 499 2 .2021 
7 1505.1 .4527 9 . 10 1 .0 . 00 + 2 2858.1 .4200 10 68 1 . 0 .00 
28800. 39932, 3939 . 3173 2918 . .9196 . 8692 498 . 5 .1708 28800. 38109. 4320 . 2694 2534 . .9409 .8701 499 1 , 1969 
i 1342.6 .4603 9 08 1 .0 .00 4 2 2854.0 .4209 10 69 1 .0 ,00 29600. 39337. 4064 . 3259 2996 . .9193 .8697 498 .8 . 1665 29 600. 37633. 4421. 2768 2601. ,9397 .8707 499 4 . 1919 1 1374.2 .4592 9 .08 1 .0 .00 4 9 2823.5 .4222 10 69 1 0 . 00 30400. 38727, 4190 . 3342 3071. .9187 .8694 498 .7 . 1623 30400. 37081. 4537 . 2841 2668 . .9391 . 8713 499 8 .1873 
3 1407.2 .4584 9 .10 1 .0 .00 4 2 2823.6 .4218 1C 70 1 .0 .00 
31200. 38125. 4313 . 3425 3145 . . 9181 .8689 498 4 . 1584 31200. 35087. 4922. 2872 2717. , 9459 .8635 497 7 . 1831 
B 1435.3 .4576 9 11 1 ,0 .00 4 B 3311.2 . 4007 10 86 1 0 .00 
32000. 37547. 4431. 3509 3219. ,9175 .8686 498 2 .1547 32000. 35000. 4940. 2949 2777 . .9416 . 8635 497 9 .1793 
6 1454.6 .4568 9 12 1 .0 .00 4 1 3137.6 .4093 10 85 1 .0 .00 
32800. 36983. 4547 . 3592 3293. . 9168 ,8682 498 0 . 1512 32800. 35000. 4940 . 3029 2837 . .9368 .8635 497 9 .1754 
2 1468.1 .4562 9 13 1 .0 .00 4 7 2938.2 ,4195 10 83 1 0 ,00 
33600. 3 5000. 4937 . 3653 3353 . ,9177 .8627 497 4 , 1483 33600. 34909. 4976. 3116 2913 , .9349 .8672 50C 2 . 1717 
5 1924.5 .4306 9 20 1 0 .00 4 0 2804 .5 .4243 10 78 1 0 .00 34400. 35000. 4937. 3738 3424 . .9158 .8627 4 97 4 . 1452 34400. 34451. 5098 . 3192 2991. .9370 .8688 502 2 .1678 8 1755.4 .4408 9 20 1 .0 . 00 4 9 2817.3 .4234 10 78 1 0 .00 35200. 35000. 4937 . 3826 3497 , . 9140 .8627 497 4 . 1422 35200. 33994. 5217 . 3267 3067. .9388 ,8698 503 8 .1642 
4 1590.5 .4511 9 20 1 0 ,00 4 6 2826.9 .4231 10 77 1 0 .00 
3 6000. 35000. 4937 . 3915 3572, .9122 ,8627 497 4 .13 92 36000. 33537. 5335 . 3341 3142 . ,9404 .8705 505 2 .1608 
6 1429.5 . 4613 9 19 1 0 . 00 4 C 2834.4 .4229 10 78 1 0 ,00 
3680O. 35000. 4963 . 4025 3677 . . 9134 .8699 501 5 . 1364 36800. 33082. 5449 . 3412 3212 . .9415 .8701 506 0 . 1575 
1 1294,2 .4638 9 14 1 0 .00 4 1 2836.1 . 4236 10 79 1 0 .00 
37600. 34966. 4982 , 4126 3767 . ,9131 .8727 503 2 .1336 37600. 32628. 5565 . 3485 3286. .9430 . 8706 507 3 .1543 
a 1160.7 .4701 9 11 1 0 .00 + 7 2842.5 .4233 10 79 1 0 .00 38400, 34379, 5133 . 4210 3858 , .9163 . 8732 504 9 .1308 38400. 32176. 5681. 3558 3359 . .9443 .8709 508 5 .1513 8 1228.2 .4664 9 12 1 0 .00 4 1 2848.0 .4230 10 79 1 0 .00 39200. 33691. 5299 , 4285 3938. .9189 .8711 505 2 .1283 39200. 31724. 5796. 3630 3432. ,9455 , 8711 509 6 .1485 
0 1323.1 .4632 9 15 1 0 .00 4 0 2852.7 ,4227 10 80 1 0 ,00 
40000. 32944. 5479 , 4359 4017. .9217 .8688 505 6 ,1258 40000. 31274, 5911. 3701 3504 , .9467 .8712 510 7 . 1457 
4 1433.7 .4588 9 18 1 0 . 00 4 6 2856.8 .4224 10 81 1 0 .00 
SUMMARY DATA FOR CRUISE SCHEDULE 2 SUMMARY DATA FOR CRUISE SCHEDULE 3 
WEIGHT ALTITUDE THRUST FUEL SFC MACH VELOCITY SPECIFI WEIGHT ALTITUDE THRUST FUEL SFC MACH VELOCITY SPECIFI 
C RATE OF CL L/D ENGINES NOX 4 C RATE OF OL L/D ENGINES NOX 
AVAILABLE REQUIRED FLOW NUMBER RANGE AVAILABLE REQUIRED FLOW NUMBER RANGE 
CLIMB OPERATING RATE 4 CLIMB OPERATING RATE 
17600. 47592. 2736. 1671 1625 . .9720 , 8636 495 3 .3049 17600. 50000. 2336 . 1715 1617 . . 9429 .8236 472 4 .2921 
1 3034.8 .4111 10 53 1 0 .00 + 0 1688.6 . 5071 10 26 1 0 ,00 
18400. 47085. 2807 . 1749 1690. .9665 . 8652 496 3 ,2935 18400. 50000. 2366. 1805 1704 . .9440 . 8379 480 6 .2820 
7 2889.2 . 4179 10 52 1 0 .00 4 7 1483.2 .5123 10 19 1 0 . 00 
19200. 46212, 2929 . 1825. 1760 . .9641 .8679 497 5 .2829 19200. 50000, 2390 , 1899 1793 . . 9440 .8497 487 4 . 2718 
1 2897.9 .4156 10 52 1 0 ,00 4 8 1262 .3 .5198 10 11 1 0 .00 
20000. 45341. 3048. 1899 . 1827 . .9617 .8695 498 7 .2730 ' 20000. 50000. 2390. 2010 1885. .9382 . 85O0 487 5 .2585 
4 2900,8 .4138 10 53 1 0 .00 4 7 940.0 ,5411 9 95 1 0 ,00 
20800. 44573. 3160 , 1969 . 1887. ,9582 .8679 497 8 .2638 20800. 50000, 2390 . 2127 1934 , . 9325 ,8500 437 5 .2457 
1 2886 .3 .4163 10. 56 1 0 .00 4 9 625.3 .5627 9 78 1 0 .00 
21600, 43872 . 3280. 2044 . 1954, . 9560 .8692 498. 5 .2551 21600. 50000. 2413 . 2239 2097 . ,9369 . 8608 493 7 .2353 
1 2 889.3 .4169 10. 57 1 0 .00 + 9 402 . 6 . 5698 9 55 1 0 . 00 
22400. 43173. 3399. 2118. 2020. .9538 .8701 499. 1 .2470 22400. 50000. 2422 . 2361 2219 . .9397 .8654 496 4 .2237 
1 2890.3 .4172 10. 57 1 0 .00 4 1 136.9 .5846 9. 49 1 0 .00 
23200. 42477. 3517. 2192 . 2086 . .9518 .8708 499 . 5 .2394 232O0, 49776, 2510. 2466 2341. . 9496 .8936 512 5 .2189 
3 2889.7 .4173 10 . 59 1 0 .00 4 1 100 .0 .5618 9. 41 1 0 .00 
24000. 41784. 3634. 2264. 2151 . .9498 . 8711 499 . 7 .2323 24000. 49186. 2603 . 2557 2430 . .9501 . 9000 516 2 .2124 
4 2887.2 .4172 10. 60 1 0 . 00 i + 5 100.0 . 5571 9 . 38 1 0 .00 
24800. 41094. 3749 . 2336 . 2215. .9478 . 8714 499 . B .2256 24800. 48546. 2690. 2643 2506. . 9482 .9000 516 2 .2060 
CO 2883.7 . 4169 10, 61 1 , 0 .00 4 0 100. C .5583 9 . 38 1 0 .00 
25600. 40418. 3863 . 2408. 2278 . , 9459 .8715 499 . 9 .2194 25600. 47912. 2776 . 2727 2581 , .9464 . 9000 516 2 . 200C 
NOT 1$ 96 15:07:53 
F16-FLOPS-OUT 
+ 0 100 . 0 , 5591 9 .39 1 . 0 .00 -f 3 2876.0 .4165 10 .63 1 .0 .00 
26400. 47286. 2861 . 2811 2655. . 9448 .9000 516 .2 ,1944 26400. 39782. 3978 . 248C 2342 . . 9444 .8715 499 .9 .2134 
4 0 100. C .5595 9 .39 1 .0 .00 4 3 2871.9 ,4166 10 .64 1 0 ,00 27200. 46666. 2945. 2893 2729. .9433 , 9000 516 .2 .1891 27200. 39288. 4073 . 2549 2401 . .9421 . 8692 498 5 . 2076 4 6 100.0 .5596 9 .40 1 .0 . 00 + 2 2828.5 .4215 10 . 67 1 .0 . 00 28000. 46053 . 3028 . 2975 2802 . . 9419 .9000 516 .2 , 1842 28000. 38667, 4205, 2622 2470. .9419 .8704 499 2 .2021 + 5 100. 0 .5594 S .41 1 0 .00 + 2 2858.1 .4200 10 ,68 1 0 .00 
28800. 45447. 3110. 3055 2874 . .9405 . 9000 516 .2 .1796 28800. 38109. 4320. 2694 2534 . .9409 . 8701 499 1 , 1969 
+ 1 100 .0 .5590 9 .43 1 .0 .00 2 2854.0 .4209 10 .69 1 .0 .00 
29600. 44868. 3193 . 3137 2946 . .9392 .9000 516 .2 . 1752 29600. 37633. 4421 . 2768 2601. . 9397 .8707 499 4 . 1919 
4 2 100.0 .5588 9 .44 1 0 .00 + 9 2823.5 .4222 10 .69 1 0 .00 30400. 44356. 3280. 3222 3022 . .9378 .9000 516 .2 ,1708 30400. 37081, 4537 . 2841 2668 . .9391 . 8713 499 8 .1873 + 2 100.0 .5600 9 43 1 .0 .00 2 2823.6 .4218 10 7C 1 0 .00 31200. 43848. 3367. 3307 3097 . .9365 . 9000 516 2 .1666 31200. 35088. 4922. 2872 2717 . 9459 .8635 497 7 . 1831 4 8 100.0 . 5609 9 .43 1 0 ,00 4 B 3310.9 .4007 10 86 1 0 .00 
32000. 43344. 3453 . 3391 3172 . , 9352 , 9000 516 2 ,1627 32000. 35000. 4940 , 2949 2777 . .9416 .8635 497 3 ,1793 
4 6 100.C . 5616 9 44 1 0 .00 4 1 3137.6 .4093 1C 85 1 0 .00 32800. 42844. 3537 , 3475 3246. .9341 . 9000 516 2 .1590 32800. 35000. 4940. 3029 2837 . 9368 .8635 497 9 . 1754 4 5 100.0 .5620 9 44 1 0 .00 4 7 2938 .3 .4195 10 83 1 0 .00 33600. 42349. 3622 . 3557 3319, . 9330 . 900C 516 2 .1555 3360O. 35000. 4952 . 3117 2911. .9338 . 8669 499 8 .1716 4 4 100. 0 . 5623 9 45 1 0 .00 4 8 2764,1 . 4264 10 78 1 0 .00 
34400. 41858, 3705 . 3639 3392 . .9319 .9000 516 2 .1522 34400. 35000. 4970. 3211 2997 . .9332 . 8717 502 6 . 1677 
+ 1 100 .0 .5623 9 45 1 0 .00 + 1 2601.5 . 4318 10 71 1 0 .00 
35200. 41371. 3788, 3721 3464. .9309 . 9000 516 2 .1490 35200. 35000, 4978 . 3302 3076. 9317 . 874C 503 9 .1638 
4 4 100.0 .5621 9 46 1 0 .00 4 2 2430.1 .4395 10 66 1 0 .00 36000. 40889. 3870. 3801 3535 . . 9300 . 9000 516 2 .1460 36000, 35000. 4988. 3395 3159 . .9304 .8767 505 5 .1600 4 4 100.0 .5617 9 47 1 0 .00 + 4 2265.2 . 4466 10 60 1 0 ,00 36800. 40410. 3951 . 3881 3 606 , .9291 . 9000 516 2 .1431 36800. 35000. 4998. 3490 3243 . 9292 . 8794 507 0 .1563 + 7 100 .0 . 5612 9 48 1 0 .00 4 6 2103.8 .4538 10 54 1 0 .00 
37600. 39944. 4033 . 3961 3677 . . 9283 , 9000 516 2 .1404 37600. 3 5000. 5008 , 3587 3329 . 9281 . 8322 508 6 .1527 
4 1 100.0 ,5608 9 49 1 0 .00 4 9 1946.2 .4607 10 48 1 0 .00 38400. 39534, 4119 . 4045 3753. .9277 .9000 516 2 . 1375 38400. 35000. 5013. 3686 3417 . 9270 .8850 510 2 .1493 4 4 100.0 .5616 9 49 1 0 ,00 + 2 1791.8 .4676 10 42 1 0 .00 39200. 39126. 4205. 4130 3829 . .9273 .9000 516 2 .1348 39200. 35000. 5027. 3787 3507. 9260 . 8877 511 3 .1459 + 1 100. 0 . 5622 9 49 1 0 .00 4 5 1640.3 .4744 10 35 1 0 ,00 
40000. 38722. 4290 . 4213 3905 . , 9268 .9000 516 2 .1322 40000, 35000. 5037 . 3889 3598 , 9251 .8903 513 3 .1426 
+ 0 100 .0 .5626 9 49 1 0 .00 + 1 1491.4 .4812 10 28 1 0 .00 
SUMMARY DATA FOR CRUISE SCHEDULE 4 SUMMARY DATA FOR CRUISE SCHEDULE 5 
WEIGHT ALTITUDE THRUST FUEL SFC MACH VELOCITY SPECIFI WEIGHT ALTITUDE THRUST FUEL SFC MACH VELOCITY SPECIFI 
+ C RATE OF CL L/D ENGINES NOX 4 C RATE OF CL L/D ENGINES NOX 
AVAILABLE REQUIRED FLOW NUMBER RANGE AVAILABLE REQUIRED FLOW NUMBER RANGE 
+ CLIMB OPERATING RATE 4 CLIMB OPERATING RATE 
17600. 47592. 2736 . 1671 1625 , . 9720 .8636 495 3 .3049 17 600 . 0. 16257. 2673 3022 . 1 1307 .5979 395 5 . 1308 
+ 1 3034 .8 .4111 10 53 1 0 .OC + 5 30911.3 . 1108 6 58 1 0 .00 
18400. 47085. 2807 . 1749 1690. ,9665 ,8652 496 3 .2935 18400. 0 . 16226. 2670 3020. 1 1309 .5953 394 1 , 1305 
+ 7 2889 . 2 .4179 10 52 1 0 . 00 4 1 29404,1 .1166 6 89 1 0 .00 
19200, 46212. 2929 . 1825 1760. . 9641 . 8679 497 a .2829 19200. 0 . 16196. 2670 3020. 1 13 08 .5939 392 S . 1301 
+ 1 2897.9 .4156 10 52 1 0 .00 4 1 28028 .4 , 1225 7 19 1 0 . 00 
20000. 15341. 3048 . 1899 1827 . .9617 .8695 498 - , 2730 20000, 0, 16173, 2675 3023. 1 1302 .5925 391 9 .1296 
+ 4 2900.8 .4138 10 53 1 0 .00 4 4 26785.5 .1282 7 48 1 0 .00 
20800. 44573. 3160. 1969 , 1887 , .9582 .8679 497 s .2638 20300. 0 . 16151. 2681 3028 , 1 1295 , 5911 391 0 . 1291 
4 1 2886.3 .4163 10 56 1 0 .00 4 2 25643.8 .1339 7 76 1 0 . 00 21600, 43872. 3280 . 2044 . 1954 , .9560 .8692 498 5 . 2551 21600. 0 . 16132. 2690 3036 . 1 1285 .5899 390 2 ,1285 + 1 2889.3 .4169 10 57 1 0 .00 4 5 24592.4 , 1397 8 03 1 0 .00 22400. 43173. 3399 . 2118 . 2020. .9538 .8701 499 1 .2470 22400. 0, 16116, 2701 3044 . 1 1272 .5888 389 5 . 127S + 1 2890.3 ,4172 10 57 1 0 . 00 4 4 23622.1 .1454 3 29 1 0 , 00 
23200. 42477, 3517 . 2192 . 2086 . .9518 .8708 499. 5 .2394 23200. 0 . 16101. 2715 3056 . 1 1255 .5879 388 9 . 1272 
+ 3 2889.7 .4173 10 59 1. 0 .00 4 8 22723.9 . 1510 8 55 1 0 .00 
24000. 41784. 3634 . 2264 . 2151 . ,9498 ,8711 499 7 .2323 . 2 4000. 0. 16093. 2736 3072 , 1 1230 .5874 388 6 , 1264 
t 4 2887 . 2 .4172 10 60 1. 0 .00 4 8 21901.1 . 1565 8 77 1 0 .00 
24800. 41094. 3749. 2336. 2215. .9478 . B714 499 a .2256 2480O. 0 . 16088, 2759 3091. 1 1202 .5871 388 4 .1256 
+ 8 2883.7 .4169 10 . 61 1 . 0 . 00 4 5 21137 .9 .1619 8 99 1 0 .00 
25600, 40418. 3863 . 2408. 2278 . .9459 . 8715 499. s .2194 25600, 0, 16086. 2786, 3112 . 1 1171 . 5870 388 3 . 1247 
15:07:53 F16-FLOPS-OUT 
+ 7 
* 7 
* 3 
+- 7 
+ 9 
t 9 
+ 8 
+ 7 
+ 0 
r 2 
* 4 
+ 6 
* 0 4-
 4 
+ 3 4
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+ 3 
+ 9 
2Q4J8.7 
264O0. 
19768.6 
27200. 
191.52.4 
2BQ00, v. 
288 DO . 
I8D41.6 
25600. 
: 40. 
30400. 
17072.2 
31200. 
36634.4 
32090. 
16220.9 
32800. 
i 321.2 
33600. 
35445,0 
34400. 
14090.6 
352OC. 
14753.1 
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14454.3 
16800. 
14108.4 
17SO0. 
13763.9 
38400. 
13432.8 
3920O. 
13114.1 
40000. 
128*7.3 
. 1721 
,1825 
.1921 
C 
.1966 C 
.2010 c 
.2053 0 
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0 
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2 2 57 
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0 
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0 
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. 2454 
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9.19 
16087. 
9.38 
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9.56 
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9 .72 
16105. 
9 .88 
36117. 
10.02 
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10 . 15 
15149. 
10,26 
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10 ,50 
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10.60 
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10 , 70 
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10 .79 
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I 62S3 . 
10,97 
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11.If 
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11 .18 I
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11.34 
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2835 . 3135 . 
1.0 00 
->, fi ,:i 6 . 3160. 
28B0. 
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1 . 0 .00 2 0 55. 3247 . 
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3215 . 3455 . 
1.0 .oo 
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33-3 . 
319 3. 
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3483 . 
367 I 1.0 .oo 3527 . 3706 . 
1.1138 
1,1102 
1.1065 
1.1026 1 ij9B5 
1 .0944 
1.0902 
1.0862 
l.C. . 
1.0784 
1.0746 
1.0707 
1 . 0663 
1 .0535 
3 , Oc 0 3 
7 .03 7 2 
1 . 054G 
1 .0508 
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. 5872 
.5376 
.5881 
.5889 
. 5898 
.5910 
. 5922 
. 5932 
.5944 
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. 5970 
• 5992 
. f.995 
.5995 
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388 .3 IRfl. 4 
188.7 
389 . 0 
3B9.5 
390. 2 
390 .9 
391.7 
302 . 4 
391 2 
394 . 1 
395,1 
39S.3 
396.6 
396.6 
396 . 6 
395.6 
396.6 
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. 1229 
.1219 
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. 1179 
. 1170 
.1160 
. 1150 
1140 
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1101 
.1090 
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.1069 1 . 0 
RUISE SCHEDULE RANGE AND TIME SUMMARY 
RANGE -2- TIME •HEIGHT 
-4- '1 Z'V-r. 
! POUNUfi 
(HE! 
40000. .00 3S600. 
11 
392DD. 
.21 
3 8800• 
.34 3. 
, 4 6 
3 8000. 
5/ 
376.00 . 
.69 
37200. 
.81 
36800. 
.94 
36400. 
1 .06 
3*000. 
1-19 
RANGE • 
RANGE -5-
(N.MI.) 
(N.MI.] 
.0 
.0 5.J
 .6 
4 2.1 
101,7 
153.2 
129.3 
201 .3 
I 11 .8 
257 . 9 
216 . 6 
'11 1 
260.5 
j64 .8 
304 .7 
419.1 
144, 0 
47 3 
393,6 
529.3 
418 .3 
. - II 
TIME 
I Kit) 
1HR) 
.00 
.00 
.10 
2. 
.30 
.33 
.72 
.77 
. 83 
.38 
.34 
.99 
1 .05 
L.ll 
[N.MI.) 
, 0 
58 . 6 
117 . 7 
177 . 4 
237 . 6 
298.5 
359.3 
422,0 
484 .7 
548 . 0 
612 .0 
[HR| 
. 00 
. 11 
.23 
. 35 
.47 
. 59 
71 
. 83 
. 95 
1 .08 
1.21 
RANGE -3- TIME 
(N.MI.) (KR) 
53 . 1 
106 . 8 
161.0 
215 .7 
271 . 0 
326 . 9 
383 . 3 
440.3 
497 . 9 
556 .D 
.OC 
. 10 
.23 
.31 
. 42 
.53 
. 63 
74 
. 85 
.96 
RANGE 
(N.MI.J 
.0 
57 ,4 
115 .4 
174 . 1 
233 .5 
293 . 6 
354 .4 
415.8 
478.0 
540 .9 
1.31 
35200 . 
1 . 44 
34600. 
1.57 
34400. 
1 .71 
34000 . 
1 . i 
31600. 
1 . 58 
33200. 
2 .13 
32800 . 
2 .76 
32400. 
2 . 40 
32000. 
2.54 
316O0. 
2 .69 
31200. 
2 , H3 
30800 . 
2 .98 
30400. 
3 . 13 
30000. 
3 . 28 
29600 . 
3.41 
29200. 
3.59 
2B800. 
3 .74 
26400. 
3 .90 
2 8000. 4 . or. 
2' 7 00. 
4 .23 
27200. 
4 .39 
2C80O. 
4 . 56 
26400. 
4 . 13 
26000 
4 .90 
25600. 
5 . 0G 
25200. 
:.. 25 
24S00. 
5,43 
24400. 5.61 
24000. 
5. "0 
236-00. 
5.99 
23200. 
5 . Hi 
22600. 
6,37 
22400, 
565-3 
433 .3 
641. 9 
528.4 
699 , L 
573 .7 
756.9 
639.3 
315. 4 
665.0 
H74 .4 
713.9 
934 . 0 
757.0 
994 .2 
801.3 
1055.0 
849. B 
111* .6 
896.5 
1178:' 
943.4 
1241.9 
990.5 
1305.6 
103 7.6 
1370 .2 
1085,3 
1415 . 6 
1113.0 
1501.S 
lit! . J 
1168.8 
1229 . t 
1636,7 
1277-1 
1705.5 
1374.5 
1545.8 
3423.1 
1917,3 
1472.4 
1959.8 
1521.7 
206 3.3 
1571.1 
2137 6 
1620. 6 
2213.3 
1670.S 
2289.S 
1720.6 
2367.6 
1770.B 
2446.5 
1B21.i 
252 6.5 
1871.6 
2607 7 
1322.3 
2690.2 
1973.: 
2773.9 
2 02 4.1 
2359 .0 
1 . 15 
1 .22 
1.26 
1.31 
1 31? 
1.45 
l.Sl 
1.56 
1,63 
1 , 68 
1 .75 
1 . t- 0 
1.87 
1.91 
1 . ?9 1-1
 . !3 
2 . 11 
2.15 
2.23 
2 . 27 
2 . 36 
2 .39 
2 . 48 
2.51 
2.61 
2 . fij 
2 . 14 
2 .75 
2 . 87 
2 .37 
3 .00 
3 . 00 
3 . 14 
1 . 12 
3.28 
3.24 
3.41 
2 , 37 
3 . 55 
3.49 
3 .70 
3 . 62 
3.84 
3.75 
3 . 99 
3.87 
4 .13 
4 .00 
4.28 
4..'.3 •1,14 
4.2b 
1. 19 
•1.71 
4 . 52 
4.91 
4 ,77 
S.23 
4.91 
5.40 
5,04 
5.57 
5. • 
5.74 
576-6 
742 .0 
806,0 
874 .8 
942.4 
1QJ0 .7 
1079 .7 
1149.5 
1220.1 
12? 1. .4 
1363 . 5 
1436 , 4 
1510 . 1 
15B4.6 
1660 .0 
1 7 •( 6 . 3 
1813 . 6 
1891 . 8 
1971 . 1 
2051 . 4 
2132 .8 
2215.3 
2298.9 
2383 .7 
2469 . 7 
255S.8 
2645.2 
2714 ,9 
2825 .8 
29IB.0 
JOIV.7 
3 3 11 6 . 7 
3203.2 
3301 . 3 
1 .33 
1.46 
1.59 
1 , 73 
1 . 86 
2 . 00 
2 .14 
2 .28 
2 . 42 
2 - 56 
2.71 
2 .85 
3.00 
3 .15 
3 .30 
3.45 
3.61 
3.76 
3 .92 
4 .08 
4.25 
4.41 
1 . 5 i. 
4.75 
4. 92 
5.27 
3.45 
5 . 63 
5 . 82 
t . 0 7 
6. 20 
4.39 
6 . 59 
614 . 7 
674 .C 
733 . 9 
794 .5 
855. 7 
917 . 6 
980.2 
1043 . 4 
1107 . 4 
1172 . 1 
1237 . 6 
1303 .9 
1371 .0 
14111. 9 
1507 , 6 
1647.8 
1719.2 
1791.5 
1864 . 8 
193S.9 
2014.1 
2090.3 
2 i -: 7 . 5 
2245.8 
2 i 15 . 2 
2405.8 
2487.6 
2571) .7 
2655•j 
2740.6 
2827.5 
2915.5 
1004.4 
1 .19 
1 .31 
1.42 
1.54 1
 . 66 
1.78 1
 . 90 
2 .02 
2 . 15 
2 .27 
2 . 40 
2 .53 
2 . 66 
3 .79 
2 , 92 
3 .06 
; . 1? 
3 .33 
3 .47 
3,61 
3 .76 
3 . 90 
4.05 
4.2!) 
4 .35 
4.50 
4 . 66 
4 . 82 
4.98 
5 . 14 
5 .31 
5 .48 
5 . 65 
5 . 83 
66B .9 
734 . 1 
800.0 
•! . . 7 
934 .2 
1002 . 4 
1071,J 
1141.3 
1211 . 8 
1283.2 
I -.55.3 
1428.2 
11C1 . 8 
1576.3 
1651 . 7 
1728.1 
1805-3 
1.3d3 . 6 
1962.5 
2043 .2 
2124.6 
2207.1 
22 3 0.7 
2375.5 
,: 4 >_• 1 . 4 
2548.6 
26.37 . 0 
2726.6 
2817.5 
jui . 6 
3003.4 
3 0=7.5 
3145.0 
3293.0 
Nov IS 96 
15:07:53 F16-FLOPS-OU1T 
+ 6.57 2075.2 5 .30 AUXILIARY TANK CAPACITY 6760.0 LB 
22000. 2945 5 5.91 3400 9 6 79 3095 1 6 01 3392 6 TOTAL FUEL CAPACITY 13735.0 LB 
+ 6 .77 2126.4 5 43 
21600. 3033 3 6.09 3502 1 6 99 3188 1 6 20 3493 8 1 MASS AND BALANCE SUMMARY PERCENT WREF 
+ 6.97 2177.8 5 56 + T LREF HORI CG-INCHES 
21200. 3122 6 6.27 3605 0 7 20 3283 2 6 39 3596 7 WING 6.11 
7.18 2229.3 5 69 + .0 .0 
20800. 3213 5 6. 45 3709 6 7 41 3380 4 6 59 3701 4 HORIZONTAL TAIL 1.45 
*- 7.39 2280.9 5 83 .0 .0 
20400. 3305 9 6.64 3 816 0 7 62 3430 0 6 80 3807 a VERTICAL TAIL 1 . 10 
+ 7 .60 2332.6 5 96 + .0 .0 
20000. 3400 0 6.83 3924 3 7 84 3582 1 7 01 3916 i FUSELAGE 10 ,56 
+ 7 . 82 2384.4 6 09 + ,0 ,0 
19600, 3495 7 7 . 02 4034 5 8 06 3686 8 7 22 4026 2 LANDING GEAR 3 .61 
+ 8 .04 2436.3 5 22 .0 .0 
19200, 3593 3 7.22 4146 6 8 28 3794 2 7 44 4138 4 NACELLE (AIR INDUCTION) 2 .01 
+ B.26 2488.3 6 35 + .0 .0 
18800. 3692 6 7 . 42 4260 8 8 51 3903 9 7 67 4252 6 STRUCTURE TOTAL ( 24.84! 
8.4S 2540.3 6 49 + ,0) ( .0) 
18400. 3793 a 7,62 4377 2 8 75 4015 7 7 90 4368 9 ENGINES 11.40 
+ 8.73 2592.5 6 62 + .0 .0 
18000. 3897 1 7.83 4495 7 a 99 4129 5 8 14 4487 5 THRUST REVERSERS .00 
+ 8.97 2644.7 6 75 + .0 186.0 
17600. 4002 3 8 . 04 4616 5 9 23 4245 3 8 38 4608 3 MISCELLANEOUS SYSTEMS ,34 
+ 9 .23 2697.1 6 88 + ,0 .0 
ITERATION 2 -
ITERATION 3 
ITERATION 4 
ITERATION 5 
ITERATION 6 
- RANGE 
- RANGE 
- RANGE 
- RANGE 
- RANGE 
1400 
596 
579 
580 
580. 
# OUTPUT FROM THE WEIGHTS MODULE 
DESCRIPTION 
WING BENDING FACTOR 
ENGINE INERTIA RELIEF FACTOR 
WINQ WEIGHT BREAKDOWN 
TERM 1 
TERM 2 
TERM 3 
WING SPAN 
WING GLOVE AREA 
HORIZONTAL TAIL AREA 
MODIFIED VOLUME COEFFICIENT 
VERTICAL TAIL AREA 
MODIFIED VOLUME COEFFICIENT 
NACELLE LENGTH 
NACELLE DIAMETER 
LENGTH OF MAIN GEAR 
LENGTH OF NOSE GEAR 
MAXIMUM LANDING WEIGHT 
WING FUEL CAPACITY 
FUSELAGE FUEL CAPACITY 
505 FOR GROSS WEIGHT = 
156 FOR GROSS WEIGHT = 
771 FOR GROSS WEIGHT = 
608 FOR GROSS WEIGHT = 
600 FOR GROSS WEIGHT = 
VALUE DIMENSIONS 
8 . 74 67 
1.000000 
1310.4 LB 
1452.0 LB 
171.0 LB 
30.00 FT 
.00 SQ FT 
63.70 SQ FT 
.936390 
54.75 SQ FT 
.268275 
31.00 FT 
2 . 81 FT 
49,90 IN 
39.00 IN 
32812.5 LB 
1144.0 LB 
5831.0 LB 
38990.23 
34390.85 
34301.90 
34306.40 
34306.36 
FUEL SYSTEM-TANKS AND PLUMBING 
.0 .0 
PROPULSION TOTAL 
.0) ( .0) 
SURFACE CONTROLS 
. 0 .0 
AUXILIARY POWER 
,0 .0 
INSTRUMENTS 
.0 .0 
HYDRAULICS 
.0 .0 
ELECTRICAL 
.0 .0 
AVIONICS 
.0 .0 
THERMAL PROTECTION 
. 0 .0 
FURNISHINGS AND EQUIPMENT 
,0 .0 
AIR CONDITIONING 
.0 .0 
ANTI-ICING 
.0 .0 
SYSTEMS AND EQUIPMENT TOTAL 
.0) < .0) 
WEIGHT EMPTY 
.0 .0 
CREW AND BAGGAGE-FLIGHT, 2 
. 0 
-CABIN, 0 
,0 
UNUSABLE FUEL 
, 0 
ENGINE OIL 
.0 
PASSENGER SERVICE 
.0 
CARGO CONTAINERS 
. 0 
1.68 
( 13.43) 
2.13 
.79 
.31 
.91 
2 .00 
7 . 11 
2 .36 
.91 
.78 
. 15 
I 17.44) 
55.70 
.63 
.00 
. 65 
. 17 
.30 
. 50 
POUNDS 
2096 . 
498, 
376. 
3624 . 
1238 , 
689 . 
8521.) 
3911, 
0. 
117 . 
578 . 
4606.1 
730. 
271. 
107 . 
311 . 
686, 
2438 . 
808 . 
312 . 
2 67 , 
53 . 
5983.) 
19110. 
215 . 
0. 
223 . 
59 . 
102 . 
172 . 
Nov IS 96 
15:07:33 
OPERATING WEIGHT 
* .0 .0 PASSENGERS, * .0 .0 
PASSENGER BAGGAGE * .0 .0 
CARGO * .0 .0 
ZERO FUEL WEIGHT 
* .0 .0 MISSION FUEL + .0 .0 
RAMP (GROSS) WEIGHT 
* . 0 .0 
57 .95 ,00 
.00 3 .11 
61.06 
38.94 
100,00 
19882. 
0 . 
0 . 
1066. 
20943. 
13358. 
34306. 
F16-FLOPS-OUT 
ACCELERATION TIME =. .0000, DISTANCE = .0000, FUEL = 
TURN * B.3197 G, OMEGA = 15.70 DEG/SEC AT CL = .80720, CE 
* 28583. LB 
TURN = 8.4536 G, OMEGA = 15.96 DEG/SEC AT CL = .80720, CD 
* 28583, LB TURN = 8.5896 G, OMEGA = 16.22 DEG/SEC AT CL = .80720, CD + 28583, LB 
TURN = 8.7277 G, OMEGA = 16.48 DEG/SEC AT CL = .80720, CD + 2 8583. LB 
TURN = 8.8681 G, OMEGA =, 16.75 DEG/SEC AT CL = .80720, CD 
* 28583. LB TURN = 9.0107 G, OMEGA = 17.02 DEG/SEC AT CL = .80720, CD <• 28583 . LB 
.0000 
.11544, THRUST 
.11544, THRUST 
.11544, THRUST 
.11544, THRUST 
.11544, THRUST 
,11544, THRUST 
» NONCRUISE SEGMENT RESULTS 
CLIMB PROFILE DATA FOR SEGMENT 1 - - - CUMULATIVE - - -WEIGHT ENERGY ALT MACH 
TIME DIST FUEL CL L/D 33796 .00 
33771 .02 33710 
.07 33649 .13 
33588 .18 33529 
.24 33471. .30 
33413. .37 33356. 
.44 33298 .51 
33240 .59 33183. 
.68 33125. .77 
33066. .88 33007, 
. .00 32947. ..12 
32886. . .27 32824. 
. .43 
24 85 
1 .8 
7. 
IC 
9492 0 10333 
2 12480 5 
14627. 8 146 16775. 
1 2 07 18922 . 4 266 
21069, 324 23216. 
2 3 82 25364. 6 439 
27511 1 497 29658 
7 555 31806 3 612 
33953. 1 670 36100 
9 729 38248 7 788 
40395 8 848 42542 
9 909 44690. 2 971 
0 .0 
o . I 1528 
. 5 3675 .9 
5822 .3 7968 
. 3 10113 5 
12258 .3 14404 
. 9 16545 4 
18694 
0 20840 .8 
22985 . 8 25131 
2 27276 3 
29421 1 31567 
.0 33712 .5 
,700 .155 7.49 .730 
.142 6.91 .756 140 6.74 
.762 149 7.07 .767 
.159 7.4C .773 170 7.73 
,780 181 8.05 .786 
193 8.37 .792 207 8.67 
.799 221 8.96 .806 . 
237 9.25 .813 255 9.52 
.820 274 9.76 .827 
294 9.98 .8"35 317 10.14 
.843 342 10.25 .851 
369 10.31 .859 400 10.26 
VEL THRUST 
4 63 .0 33787 433,1 
33724 497 . 4 32576 
4 97 .4 31063 497 . 4 
29576 497.4 28099 
497 .S 26657 497 .5 
25138 497 .6 23644 
497 . 6 22066 497 ,7 
20464 497 .7 18935 
497 .7 17481 497 .8 
16026 497.8 14792 
497 . 9 13541 497 .9 
12433 498 .0 11366 
RCI PC /TMAX 
40622. 1 1.000 41777. 1 
1 .000 41206. 1 1 . OOO 
39378. 1 1.000 37548. 1 
1 .000 35698. 1 1.000 
33869. 1 1.000 31884. 1 
1.000 29903. 1 1.000 
27771. 1 1.000 25576. 1 
1 . 000 23465. 1 1.000 
21439. 1 . 1.000 19379. 1 
1.000 17621. 1 1.000 
15803. 1 1.000 14171. 1 
, 1.000 12549. 1 1.000 
- - INCREMENTAL- -TIME DIST FUEL 
CLIME PROFILE DATA FOR SEGMENT 13 - - - CUMULATIVE - - -WEIGHT ENERGY ALT MACH 
TIME DIST FUEL CL L/D 
,00 .02 
. 05 ,05 
.06 .06 
,06 .07 
.07 ,07 
.08 .09 
.IC .11 
. 12 .13 
.14 .16 1.0 1 .1 
1.3 
.0 24 .1 
61.4 61 .4 
60 .4 58.9 
58 .2 57 .8 
57.6 57 . 6 
57.6 57.7 
58 . 0 58 .4 
59.0 59.3 
60 . 9 62 .4 
725. S 790.2 
800 .7 751.1 
703 . 9 S59 .2 
616.7 576.3 
537 .9 501,6 
467 .1 434 . 5 
403.7 374 .6 
347 .1 321.2 
296 .8 273.9 
20905. .00 20873, 
,04 20833 . . 09 
20792. . 15 20752. 
.22 20712. . 23 
20672. .37 20632. 
.46 20591, .57 
20550. . 68 20508. 
.81 20465. .96 
20420. .14 20389, 
.28 
24612 .0 26676 
.0 29184 ,2 
31693 .5 
1000C .0 15702 
31.9 18213 72.2 
20722 112.4 
1.8 
34202. 23229 8 152.5 36710. 25735 
3 192.6 39219. 23242 232,8 
41728. 30749 2.5 273.2 44236. 33255 
3.2 313.8 46745. 35762 4.0 354.9 
49254. 38268 5.1 396.7 51762. 40775 
6.2 439.8 54271. 43281 7.7 484.4 
55959. 44967 B.8 515.7 
084 135 
146 159 
173 186 
205 225 
246 270 
303 341 
384 415 
900 4.39 .797 
7 . 06 ,805 7.46 
.813 7 .36 821 
8.27 830 8 . 68 
838 9 .09 848 
9 .47 857 9.79 
867 10,02 368 
10.31 869 10.52 
B69 10.59 869 
10 . 55 
VEL RCI 
THRUST /TMAX 574.5 66291. 
28583. 1.000 497.9 47719. 22713. 1.000 
497.8 43641. 20828. 1.000 497.8 39698. 
19019, 1.000 497.9 35973. 17319, 1.000 
497.9 32369. 15683. 1.000 497,9 29171. 
14233. 1.000 498.0 26057, 12838. 1.000 
498.0 23256. 11597. 1.000 498.1 20482. 
10396. 1.000 498.1 17809. 9229, 1.000 
498.2 15214. 8118. 1.000 498.2 12948. 
7169. 1.000 493.3 11376. 6530. 1.000 
- - INCREMENTAL- -PC TIME DIST FUEL 
.00 .0 .0 
.04 .05 
.07 .07 
.08 .09 
.10 . 11 
.13 .15 
ITERATION 7 -- RANGE 5EO.60O FOR GROSS WEIGHT 
.9 1 . 0 
1.2 
40.3 
40. 2 
40.1 
40. 2 
40 . 6 
41 .9 43 . 0 
31 .3 
34306.36 
Q 
825 .3 516.2 
475.0 436.5 
400.5 366.8 
335.4 306.1 
278 .7 253 .3 
225.5 200,1 
177 . 5 163 .7 
» PERFORMANCE CONSTRAINT SUMMARY NO. TYPE VALUE + UDE CONSTRAINT 
1 16 ACCL TO 1.400 = * 00. .087495 
2 8 MAX LOAD FACT = 
LIMIT WEIGHT MACH ALTIT .875 MIN 
3.162 GEES .000 28963. .000 28963, .800 300 .900 300 
Nov 18 96 
15:07:53 F16-FLOPS-OUT 
00. -.316199 
3 12 EXCESS ENERGY =• 
00. -20.495320 
4 9 MAX INSTAN NZ = 
00. -.517726 
5 8 MAX LOAD FACT = 
00, -.364412 
20495.3 FT/MIN 
5 . 177 GEES 
3.644 GEES 
.0 23963. .900 300 
.000 28963. .900 300 
.000 25552. 1.200 300 
# SIZING AND PERFORMANCE RESULTS 
CONFIGURATION DATA AFTER RESIZING (IF ANY) 
OPERATING WEIGHT EMPTY 
PAYLOAD 
MAXIMUM FUEL 
GROSS WEIGHT 
REFERENCE WING AREA 
WING LOADING 
THRUST PER ENGINE 
ENGINE SCALE FACTOR 
THRUST-WEIGHT RATIO 
19882.0 LB 
1066.0 LB 
13358.4 LB 
34306.4 LB 
300.00 SQ FT 
114.35 LB/SQ FT 
24850.0 LB 
1 . 0000 
,7244 
H NUMBER 
SEGMENT 
T END 
TAXI OUT 
TAKE OFF 
.300 
CLIMB 
0 .859 
CRUISE 
8 .869 
HOLD 
0 .900 
RELEASE 
0 .900 
ACCEL 
0 . 900 
TURN 
0 .900 
TURN 
0 . 900 
TURN 
0 .900 
TURN 
0 .900 
TURN 
0 . 900 TURN 
0 .90C 
RELEASE 
0 . 900 
CLIMB 
0 . 869 
CRUISE 
9 .868 
HOLD 
4 .300 
INITIAL 
ALTITUDE(FT) 
WEIGHT(LB) 
START END 
FUEL(LB) 
NOX EMISS(LB) 
SEGMT TOTAL SEGMT 
SEGMT TOTAL 
MISSION SUM 
TIME(MIN) 
TOTAL 
MARY * * * 
DISTANCE(N MI) 
34306, 
34201. 
0 . 
33796. 
0. 33712. 
32824. 
36924. 38119. 
31208. 
43843. 47951. 
255S2. 
47951. 47951, 
24023, 
10000. 10000. 
24023. 
lOOOO. 10000. 
23642, 
10000. 10000. 
23268. 
10O0O. 10000. 
22900. 
10000. 10000. 
22537, 
10000. 10000. 
22181. 
10000. 10000. 
22073. 
10000. 10000. 
20905. 
10000. 44967. 
20389. 
44967. 46150. 
19257. 
0 . 0. 
106 , 
405. 
971. 
1616 , 
5656 . 
0. 
0. 
380 . 
374 . 
368. 
362 . 
357 , 
107 . 
0. 
516 . 
1132 , 
1007 , 
106. 
511 . 
1482 . 
.00 
3098 . 
.00 
8755. 
.00 
8755. 
. 00 
8755 . 
. 00 
9135 . 
.00 
9509 . 
.00 
9878 , 
,00 
10240. 
.00 
10597. 
.00 
10704. 
,00 
10704. 
.00 
11220. 
.00 
12352. 
.00 
13358, 
. 00 
.00 
, 00 
.00 
.00 
. 00 
.00 
.00 
.00 
,00 
.00 
.00 
,00 
.00 
.00 
.00 
6.5 
.5 
1.4 
30.1 
120 .0 
.0 
,0 
.4 
.4 
. 4 
.4 
.4 
.1 
,0 
1 .3 
37.5 
20.0 
6.5 
7.0 
8.4 
38.5 
158 . 5 
158.5 
158.5 
158.9 
159.3 
159.7 
160. 0 
160.4 
160.5 
160. 5 
161.8 
199 .3 
219 . 3 
SEGMT 
10.2 
250 .0 
. 0 
.0 
.0 
. 0 
,0 
.0 
.0 
.0 
,0 
.0 
8.8 
311 . 6 
.0 
TOTAL STAR 
10.2 
260.2 
260.2 
260 .2 
260 .2 
260. 2 
260 .2 
260.2 
260.2 
2 60.2 
260.2 
260.2 
269.0 
580. 6 
580. 6 
,70 
.86 
. 90 
. 90 
.90 
.90 
. 90 
.90 
.90 
,90 
.90 
.90 
.90 
,86 
.59 
DESCENT 
+ 0 .300 
RESERVES 
TAXI IN 
ZERO FUEL 
18250. 
0. 
18250, 
18250. 
13358 . 
.00 .00 
13358. 
.0 219.3 
.0 219.3 
DESIGN RANGE 
FLIGHT TIME 
580.6 
212 .3 
BLOCK TIME = 3.65 HOURS 
BLOCK FUEL = 13358.4 POUNDS 
TOTAL NITROGEN OXIDES EMISSIONS 0. POUNDS 
78.8 NAUTICAL MILES ATA TRAFFIC ALLOWANCE = 
AIR MANEUVER = 49.8 
AIRPORT TRAFFIC ALLOWANCE = 17.4 
AIRWAY DISTANCE FACTOR = 11.6 
ATA RANGE = 580.6 NAUTICAL MILES 
#OBJ/VAR/CONSTR SUMMARY 
FUEL RANGE VAPP FAROFF FARLDG AMFOR 
+ SW TR SWEEP TCA VCMN CH W/S 
13358.4 580.6 134.9 4506. 6328. 14091. 
+ 300.0 .228 30.00 .0400 .800 50000. 114.4 
SSFOR GW 
T/W 
16923. 34306.4 
.724 
AR THRUST 
3.000 24850.0 
Appendix H Page 61 
Appendix H. Side-by-Side Assessment Details 
1. Portability 
What computer platform does the program need? 
What other supporting software, if any, does the program need? 
What other equipment are required to run the program (i.e. specific graphics library)? 
Is the code proprietary? 
2. Ease of Module Change-Out 
How easy is it to change out or add an analysis module in the source code? 
3. Optimization 
How many design variables can the optimization routine handle? 
Can one insert or select the optimization variables? 
Is the optimization scheme parametncally based? 
4. RCS/IR (Radar Cross Section/InfraRed) 
Does the code have the ability to analyze/predict the RCS/IR characteristics of the 
aircraft? 
5. Geometric Modeling 
What sort of geometric modeling does the program need, if any? 
What sort of geometric modeling capability does the code have? 
Does the code have the ability to import geometric models? 
6. Customer 
What kind of customer does the program have? 
Appendix H Page 62 
How many of these customer are "satisfied customers?" 
What future capabilities does the customer desire? 
7. DOCUMENTATION 
How well is the program documented (i.e. theory, users, application manuals)? 
8. LEVEL OF DESIGN 
What level of design (i.e. conceptual, preliminary, or detailed) can the program handle? 
9. CONSISTENCY OF FIDELITY OF ANALYSIS 
Are the analysis modules consistent in fidelity? 
Is there a way to check for consistency? 
10.TRENDS IDENTIFICATION 
Does the program/modules/equations give the correct trends when the appropriate 
design variable are perturbed? 
11. INPUT 
Are the input variables logical or are they cryptic? In other words, how easy or 
understandable are the input values? Is further analysis (off-line) required to generate 
some input? 
12.PROGRAM LIMITATIONS 
What are some of the limitations of the program (i.e. can it handle supersonic cruise 
and/or low speed flight conditions)? In other words, can the modules predict 
reasonably the data the program needs? 
For what range of conditions are analysis module results valid? 
Appendix H Page 63 
13.No Fudge Rule 
How easy is it to correlate the modules? 
What are the "fudge" factors involved in correlating models? 
14. Ease of Use of the Graphical User Interface (GUI) 
Is the GUI user friendly? 
15. Readability, Traceability, and Tailorability of Source Code 
How well is the source code commented? 
How difficult is it to trace the prograimriing logic? 
How easily can the source code be tailored? 
16. Flexibility 
How many and what type of vehicle classes can the program handle? 
17.Computational Time 
How long does the program take to execute a typical model (CPU time)? 
18.Constraint and Design Variable Sensitivity 
How well does the program predict the design sensitivities to perturbation of design 
variables subjected to constraints? 
Appendix I Page 64 
Appendix I. IPPD Methodology 
The ASDL IPPD methodology is based on an overall perspective of achieving 
customer satisfaction through robust design simulation. Robust design uses a systematic 
approach to find the optimal design factor settings which result in economical designs with 
low variability. The essential elements and goals of robust design simulation are illustrated 
in Figure 20. Traditionally, design is comprised of a simulation code (sizing/synthesis or 
economic analysis) and an optimization routine which varies the design or economic 
variables (i.e. aspect ratio, wing loading, return on investment, etc.) to yield an "optimum" 
solution subject to all imposed environmental and design constraints. 
Robust Design Simulation 
Subject to 
Technology Infusion 
Product Characteristics (disciplines) 
Process Characteristics (manufacturing, 
Producibility) 
Design & Environmental 
Constraints 
Synthesis & 
Sizing 
Economic 
Life-Cycle 
Analysis 
T 
Economic & 
Discipline 
Uncertainties 
ies P Business Practices 
Technological & 
Schedule Risk 
Robust Solutions 
Objectives: Optimum Performance Lower Acquisition Cost 
Higher Profit Higher Quality Increase Reliability 
Reduced O&S Cost Reduced Variability 
o 
Customer 
Satisfaction 
Figure 20. EPPD through Robust Design Simulation 
The identification of key product and process characteristics, as well as their relative 
contributions to the chosen evaluation criterion in the presence of risk and uncertainty, is an 
essential element of the proposed robust design simulation depicted in the figure. Robust 
Design accounts for manufacturing issues (i.e. process characteristics) and risks associated 
with new technologies. These can be measured in terms of confidence and readiness levels 
Appendix I Page 65 
(i.e., concept feasibility, producibility, and potential of fielding according to the program 
schedule). In addition, Robust Design allows for variability due to uncontrollable factors 
(economic uncertainty, noise factors, etc.). In this way, a product is designed and 
optimized concurrently, yielding a probability distribution for the evaluation criterion, 
rather than a single point design solution as is the case with traditional methods. In short, 
the objective of RDM is to find the combination of variable settings and levels which: 
• Quantify the relationship between a response characteristic and the selected 
independent variables. 
• Reduce response variability attributable to the defined noise factors. 
• Establish a product design which displays superior performance and also 
possesses low technology risk components and materials. 
The Response Surface Methodology (RSM) is one of the elements comprising 
ASDL's Robust Design Methodology. It is based on a statistical approach to building and 
rapidly assessing empirical models. By careful design and analysis of experiments or 
simulations, the methodology seeks to relate and identify the relative contributions of the 
various input variables to the system response. In most cases, the behavior of a measured 
or computed response is governed by certain laws which can be approximated by a 
deterministic relationship between the response and a set of design variables. Usually the 
exact relationship between this response and the design variables is either too complex or 
unknown, and an empirical approach is necessary to determine it. The strategy employed 
in such an approach is the basis of the RSM. For this study, a second degree model in k-
variables is assumed to exist. This second order polynomial for a response, R, can be 
written as: 
k k k [ = 1  = ] 
where, 
• bi are regression coefficients for linear terms 
Appendix I Page 66 
• bfi are coefficients for pure quadratic terms 
• bij are coefficients for cross-product terms (second order interactions) 
• xj are the design variables and xjxj denotes interactions between two design 
variables 
Once this equation is constructed, it can be used in lieu of more sophisticated, time 
consuming codes to predict and optimize the response of a sub-system or the entire system. 
The "optimal" settings for the design variables are identified by finding the maximum or 
minimum of this equation, and a confirmation case is run using the actual simulation code 
to verify the results. Since the Response Surface Equation (RSE) is in essence a regression 
curve, a series of experimental or computer simulation runs need to be performed to obtain 
a set of data for varying inputs. 
£- /£- Alii 
TITLE: SYSTEM DEFINITION AND MODULE DEVELOPMENT FOR A 
COMPREHENSIVE AIRCRAFT SIZING AND SYNTHESIS 
TOOL 
REPORT: PERFORMANCE REPORT 
PERIOD: JANUARY 19,1997 - JANUARY 18,1998 
Submitted to: 
NASA Langley Research Center 
Mail Stop 126 
Hampton, VA 23681-0001 
Technical Contact: Dr. Gary L. Giles 
Sponsor Contact: Ms. Marcia Poteat 
NAG-1-1786 
I Submitted By: 
} 
Dr. Dimitri N. Mavris 
AEROSPACE SYSTEMS DESIGN LABORATORY 
SCHOOL OF AEROSPACE ENGINEERING 
GEORGIA INSTITUTE OF TECHNOLOGY 
A Unit of the University System of Georgia 
Atlanta, GA 30332-0150 
I 
November 11,1997 
SUMMARY OF CONTRACT PERIOD EFFORTS 
Prior tasks examined the monolithic FLOPS and ACSYNT synthesis and sizing programs at the 
program level through a comparison of program results for three configurations. The program 
predictions could be matched fairly accurately for the chosen c»mmercial transport, military 
transport and fighter. However, the programs did not compare very well for baseline (non-
matched) data for a mturistic fighter and transport configurations. This is indicative of the manner 
in which metrics for individual disciplines are calculated within the codes. This year's efforts are 
focused on examining each of the codes at the subroutine level to assess the prediction capability at 
the discipline level as well as to learn more about the manner in which the sizing program actually 
sizes configurations, a potential problem area for futuristic concepts that do not necessarily obey 
historical trends. 
Teams were tasked with documenting the theory, perceived accuracy, and calculation /program 
flow and logic for each of the modules/disciplines within ACSYNT (v 4.0) and FLOPS (v 5.85). 
With the exception of the engine modules, the subroutines cannot be executed and compared 
without a substantial amount of receding. Coding efforts are to be recommended in this phase of 
the contract and carried out as the third year's tasks. The subroutines that are compared are listed 
in Table 1 below. Additional subroutines are available for both ACSYNT and FLOPS; current 
efforts are focused only on traditional and necessary sizing and synthesis modules. 
Recommendations for specific subroutines will be available in the yearly report to be ready in 
January. This recommendation will direct the larger sizing and synthesis tool developments. 
Table 1. Modules Studied for ACSYNT and FLOPS 
ACSYNT FLOPS 
Aerodynamics 
Propulsion 
Main/ControVC^timization 
Performance/Trajectory 
Stability & Control 
Weights/Structures 
Aerodynamics 
Propulsion 
Noise 
Main/Control/C^tirrdzation 
Performance 
Takeoff/Landing 
Weights/Structures 
It is noted that the overall system data is for ACSYNT Version 3.0 and the subroutines are 
documented for Version 4.0. This change is due to the availability of source code. This study 
should not be affected by the change. 
Page 1 
&3 
Title: System Definition and Module Development for 
Comprehensive Aircraft Sizing and Synthesis 
Report: Summary of Research 
Period: 19-JAN-1996 through 18-JAN-1999 
Submitted to: 
NASA Langley Research Center 
Mail Stop 126 
Hampton, VA 23681-0001 
Technical Contact: Mr. Paul Gelhausen 
Sponsor Contact: Ms. Marcia Poteat 
NAG-1-1786 
Submitted by: 
Dr. Dimitri N. Mavris 
AEROSPACE SYSTEMS DESIGN LABORATORY 
SCHOOL OF AEROSPACE ENGINEERING 
GEORGIA INSTITUTE OF TECHNOLOGY 
Atlanta, GA 30332-0150 
April 5,1999 
D. Mavris, PI, NAG-1-1793 
' 1 
D. Mavris, PI, NAG-i-1793 2 
( 
SUMMARY OF RESEARCH CONDUCTED UNDER THIS GRAM 
Overview 
The goal of synthesis and sizing in aircraft design is to create an aircraft capable of completing a 
given mission. Over the term of this grant, research has led to a further underslanding of the 
current synthesis and sizing tools FLOPS and ACSYNT as well as the development of future 
tools. All results were transferred to the Techr ical Monitor at a meeting that took place October 
16&17 at Georgia Tech. 
Research Path and Findings 
Each year of research focused on different aspects of the study. In the first year, the FLOPS and 
ACSYNT synthesis and sizing codes were decomposed into their component modules. These 
modules were then examined for content and tested with both conventional and unconventional 
aircraft. The synthesis and sizing codes were validated on the conventional cases but deviated 
highly with revolutionary concepts. i ; second year of the study focused on further 
decomposition of individual component modules of the synthesis and sizing codes and 
identification of physics based higher fidelity models to improve the accuracy and capability of die 
programs. Finally, an in-depth module study and link to the design process was completed in the 
third year of the •. idy. 
In the final year, researchers examined higher fidelity tools and developed and integrated an 
aerodynamics process. This process was meant to be a portion of a future synthesis and sizing 
code. Additionally, researchers examined the ease of using the tools in an advanced design 
environment. Techniques such as FasL Probability Integration (FPI) and Response Surface 
Methodology (RSM) were each tested and applied to test HSCT design scenarios. The IMAGE 
infrastructure, developed by Dr. Mark Hale of the Aerospace Systems Design Laboratory at the 
Georgia Institute of Technology, was used as a framework for integration of many of the test tools 
and methodologies. The integrated IMAGE platform was then applied to the sample design of a 
High Speed Civil Transport (HSCT) and the incorporation of higher-fidelity aerodynamic tools 
into the synthesis and sizing process were examined. Specifically, this process includes the use of 
VORLAX, W1NGDES, and BDAP. These tools are often used to augment or replace low fidelity 
analyses during the synthesis and sizing procedure. 
Components of IMAGE as well as tools developed by researchers for an advanced synthesis and 
sizing tool were delivered as follows: 
Category Tool Description 
Analyses ALCCA (v3) Life Cycle Cost 
FLOPS (v5.94) w/ASDL additions Aircraft Synthesis and Sizing 
Design FPI Fast Probabilistic Integration 
STARS (v4.0) Response Surface Calculation 
Command DOE (v4.0) Parallelized Response Surface Calculation 
"IMAGE (V1.14) w/test cases Design environment 
Utilities doe2rse Etetenriination of RSE coefficients for quadratic 
equations 
parse (v98) Parse formatted output file 
plotcdf (vl.14) Plot cumulative distribution functions 
tsw Substitute into FORTRAN namelist file 
The research led us to conclude that integral ties between synthesis and sizing and high-fidelity 
analyses capability is needed for the analysis and design of revolutionary configurations. The 
discipline core modules need to include disciplines such as stability and control, safety, and 
economics. Also, an expansion of basic mission driver must be done to include such things as 
changing sizing criteria, constraint checking, and rules. The synthesis and sizing code must also 
facilitate emerging design methods such as the use of approximations, optimization, and 
probabilistic techniques. 
All the above activities were reported to the technical monitor directly in a visit on October 16 and 
17, 1998 at Georgia Tech. A description of the tools has been made accessible through a web 
interface (password protected and given to the sponsor) located at: 
http://www.asdl.gatech.edu/langley 
D. Mavris, PI. NAG-1-1793 3 
Publications I 
DURING THE THIRD YEAR, THE ADVANCED SYNTHESIS AND SIZING TOOLS HAVE BEEN REFINED, FORMALIZED, AND EXPANDED TO INCLUDE HIGHER FIDELITY TOOLS AND TECHNIQUES. THE MAJORITY OF THIS WORK HAS BEEN 
SURNMARIZED AND (HSSEMINATED IN TWO CONFERENCE PAPERS, AND THEY ARE LISTED BELOW. THESE PAPERS ARE ALSO DOWNLOADABLE FROM THE ASDL WEB SITE AT: HTTP://WWW.ASDL.GATECH.EDU. 
I 1. TEJTEL, D., M. A. HALE, AND D. N. MAVRIS, "CONCEPTUAL AIRCRAFT DESIGN ENVIRONMENT: CASE 
STUDY EVALUATION OF COMPUTING ARCHITECTURE TECHNOLOGIES," 7TH AIAA/USAF/NASA/ISSMO SYMPOSIUM ON MULTIDISCIPLINARY ANALYSIS AND OPTIMIZATION, ST. LOUIS, MO, SEPTEMBER 2-4, 
1998. AIAA-98-4844. 
2. EL AICHAOUI, S., M. A. HALE, AND J. I. CRAIG "BUILDING DESIGN APPLICATIONS USING PROCESS ELEMENTS," 7TH AIAA/USAF/NASMSSMO SYMPOSIUM ON MULTIDISCIPLINARY ANALYSIS AND 
OPTIMIZATION, ST. LOUIS, MO, SEPTEMBER 2-4, 1998. AIAA-98-4876. 
D. Mavris, PI, NAG-1-1793 
I 4